Utter system for multiple use of the space-rockets equipped with spreadable-arms and possibly more devices, and method of these space-rockets vertical landing by hanging on landing-station having movable gantries and more apparatus.

ABSTRACT

Utter system for multiple use of the space-rockets equipped with spreadable-arms and possibly more devices, and method of these space-rockets vertical landing by hanging on landing-station having movable gantries and more apparatus. The space-rockets can have steering flaps, a dividable sectional-load-cover, a sliding-engines-cover having jalousies. The landing-station can be on land or can be deck-mounted on ship. The landing-station must have the movable gantries and can have hangers and grasping-wagons. The hangers can have rotating-wedges. The gantries can have damping-wagons. On landing-station can land and be fasten a few space-rockets in short time intervals. The ship can comprise a few joined hulls, horizontally movable-decks, ballasting-wagons. The utter system can comprise a harbor terminal for space-rockets reload and launch and which can have movable ground-gantries and ground-crane. The utter system allows that the space-rockets can liftoff from two movable gantries whilst these space-rockets vertically hang on their spreadable-arms.

TECHNICAL FIELD OF THE INVENTION

The present invention and its disclosure is directed generally to some space-rockets overall applying and usage, and their associated systems and methods.

BACKGROUND OF THE INVENTION

Since long time ago the space-rockets are applied and used. Nonetheless to this day one did not invent some system of space-rocket launching and landing which in fullness would recover it, and would be very reliable, secure, trouble-free in the usage and simultaneously would enable the same space-rocket liftoff several hours after its landing. And nowadays, particularly the space-rocket landing is very problematic. Currently a few companies land the space-rocket first stages on some spreadable legs which has several disadvantage. Such landing is very uncertain because sometimes the space-rocket fall over. And in the event of the one leg failure the whole space-rocket will surely fall over. Landing on legs make it impossible to utilize some damping mechanisms in legs because they would surely cause the space-rocket fall over. While on other hand the lack of some damping mechanisms in legs can cause their breakdown. Sometimes after the landing the space-rocket stand slanted and can also suddenly fall over. That is problematic situation and danger for some working personnel as well. During the landing, the space-rocket legs can be spread out only in the last seconds of the space-rocket descent so that do not cause the space-rocket leaning on some side. The inclined space-rocket will not stand up on legs or will broke one leg. And anyway the legs cannot be spread out earlier because the air strong flow is in opposite direction. And during such landing, the space-rocket legs are spread among white-hot flames exhausting from the main engines. Next these flames also rebound from a landing pad toward the legs thus during all this time they are burned and destroyed in part. Consequently the legs have to stand on landing pad that is in white-hot flames. The landing on legs makes impossible the application of very long space-rockets or, so that these space-rockets would have mounted on top some modules or loads. The landings on legs requires almost windless weather conditions because even moderate wind can cause the space-rockets fall over and their total loss. As result comes conclusion that at windy conditions the space-rockets can not liftoff because later they will not be able to land on legs. And it causes that sometimes the space-rockets having legs must wait several days for possibility of launch. Suchlike problems are not at landings on some spreadable-arms. The spreadable legs installed in the space-rocket bottom make it impossible for installing there some foldable thermal cover of the main engines. Like it is presented in current invention. As a result, currently the space-rocket first stage landings on legs have characteristic of the continuous attempts and therefore all landings are treated as the secondary purposes of all space-rockets launching. Whereas plenty other companies do not endeavor space-rocket landings at all. Furthermore for security reasons it is recommended so that all space-rockets landings would take place on ships at sea. And for this reason the space-rocket landings on legs on rolling ships are worse uncertain. Earlier were applied Space Shuttles which had plenty advantages, rather secure landing although unsafe liftoff. However the Space Shuttles had very large and heavy wings and furthermore some heavy wheels with suspension. The large wings extorted usage of the complex and heavy thermal cover of whole Space Shuttle. As a result of some disadvantages and high operating costs the Space Shuttles one withdrew from the use. All-in, currently all over the world there are no possibilities of the return and regain from the Earth's orbit entire space-rockets or any overall loads. Yet, there are applied some small capsules which return from the Earth's orbit by means of parachutes. This is very primitive solution. All these mentioned disadvantages of currently known and applied solutions of the space-rockets launching and landing does not have presented here invention.

SUMMARY OF THE INVENTION

This invention is the utter system for multiple use of the space-rockets equipped with several spreadable-arms and possibly more devices. This utter system includes the method of these space-rockets vertical landing on landing-station having movable gantries and more apparatus. The landing-station can be on land or can be deck-mounted on ship. The landing-station must have the movable gantries and can have hangers and grasping-wagons. The ship with deck-mounted landing-station have two movable deck-gantries with several damping-wagons whereon the space-rockets vertically land as hang themselves on their spreadable-arms. The ship with deck-mounted landing-station can also have four hangers, two grasping-wagons. On current deck-mounted landing-station can land three space-rockets in a few minutes intervals and two first can be quick moved on hangers and fasten. The third landed space-rocket remains on both deck-gantries and is fastened by both grasping-wagons. As result each space-rocket landing is super safe. This utter system is completely connected with utilization of several spreadable-arms mounted on all space-rockets. Therefor these spreadable-arms are the main characteristic feature of this utter system. Furthermore each space-rocket vertical landing can occur with some attached modules and return-load and this feature is very important possibility and advantage of this utter system. Therefor this utter system includes that all space-rockets and their sub-assemblies and modules are designed and destined for multiple use thus return with the space-rockets on Earth.

This utter system comprises that on each space-rocket can also be cardinally installed four steering flaps, the dividable sectional-load-cover and the sliding-engines-cover having jalousies.

This utter system comprises the ship having deck-mounted landing-station and furthermore this ship has also several joined hulls, two horizontally movable-decks, two ballasting-wagons.

Moreover this whole utter system comprises also the harbor terminal for three jointed space-rockets launch preparation, liftoff and later unloading from the ship. The harbor terminal has two movable ground-gantries and one movable ground-crane. Therefor this utter system includes also that several jointed space-rockets during hanging on two ground-gantries can be launch prepared in vertical position thus whilst they vertically hang on their spreadable-arms. And next these three jointed space-rockets can liftoff from these two ground-gantries thus whilst they vertically hang on their spreadable-arms as well.

All together, in current utter system are presented processes of three jointed space-rockets liftoff, jointed ascent, their separation, further separated ascent, deployment of a load, docking of a return-load, descent and vertical landing on ship with landing station.

In this utter system more exact description of the space-rocket design and its action and multiple use is following. In this utter system each space-rocket vertically lands as hangs itself on its spreadable-arms. Therefor each space-rocket has installed these sophisticated several spreadable-arms. And moreover each space-rocket can have cardinally installed sophisticated four steering flaps, the dividable sectional-load-cover and the sliding-engines-cover that can be flat underneath or wedge-shaped underneath.

On space-rockets mounted spreadable-arms are absolutely necessary and are utilized multiple times. These spreadable-arms create many possibilities. First of all and the most important is that each space-rocket lands on its spreadable-arms as hangs itself on them. Before landing, all spreadable-arms are used as an aerodynamic brake during the space-rocket descent in the Earths atmosphere. Because all spreadable-arms are designed and build as very strong therefor during space-rocket descent, they can be lifted upwards (spread out) on very high altitude for use as the aerodynamic brake. As result of long-lasting aerodynamic braking caused by spreadable-arms, it will be necessary to use far less space-rocket fuel at landing engine burn. These spreadable-arms are mounted on each space-rocket upper part. The quantity of spreadable-arms mounted on each space-rocket depends on its weight. Therefor currently in one booster-space-rocket are mounted six spreadable-arms and in one main-space-rocket are mounted ten spreadable-arms. These spreadable-arms are suitably spaced out in each space-rocket fuselage so that they all could completely spread out on two sides. Whereas all spreadable-arms are entirely lowered down, they are alongside the space-rocket fuselage. Whereas all spreadable-arms are entirely lifted upward, they are completely spread out and are transverse the space-rocket fuselage. Each spreadable-arm is moved by one moving mechanism installed inside the space-rocket fuselage. Each spreadable-arm consists of two lateral-beams and one middle-beam and additional sub-assemblies. And above each spreadable-arm moving mechanism is installed a pushing mechanism having a blocking-bar which serves for blocking the middle-beam in spreadable-arm whilst it is entirely lifted up. In maximally slid outside location the blocking-bar fulfills its main purpose that is total blocking the middle-beam in all directions. The middle-beam after its blocking gains possibility of carrying burdens in all directions.

Four steering flaps are cardinally installed on each space-rocket upper part as well. These flaps serve for steering the space-rocket descent in the Earth's atmosphere. All flaps are in large sizes so that they could steer the space-rocket descent even at low speeds. Two opposite flaps have additionally rotary installed some torsional-triangles which serve for precise steering of entire space-rocket axial torsion, needed before landing on two deck-gantries.

The sectional-load-cover is dividable into two sections and gradually foldable out on two opposite sides. And later this sectional-load-cover can be gradually folded up by pooling together up to total shutting. The sectional-load-cover serves for covering inside some load and this way creates its thermal protection during the space-rocket ascent and descent in the Earths atmosphere. Thus inside the sectional-load-cover can be fastened some load that will be carried out on Earth's orbit and later can be fastened some return-load that will be carried down on Earth. The sectional-load-cover is revolvingly installed on main-space-rocket upper part and can be situated above the second-stage-rocket. The sectional-load-cover can be completely lowered down to main-space-rocket upper part as well. Each one section of the sectional-load-cover is held up and incline by two cog-beams. All four cog-beams are long and are revolvingly installed to main-space-rocket upper part. Whereas the sectional-load-cover is shut up then all cog-beams are outside and on both sides of the second-stage-rocket. The sectional-load-cover can be lifted somewhat above the second-stage-rocket before folding out on two opposite sides.

The sliding-engines-covers can be flat underneath or wedge-shaped underneath after their lowering down. Each sliding-engines-cover serves for covering the space-rocket main engines and this way creates their thermal protection during the space-rocket descent in the Earths atmosphere. Both sliding-engines-covers can be rapidly shut down (by sliding down) or rapidly opened (by sliding up). Each sliding-engines-cover consists of a main-cover having two sliding jalousies and consists of two sliding rounded-plates.

In this utter system more exact description of the landing-station design and its action and multiple use is following. In this utter system, the ship comprises deck-mounted landing-station having two movable deck-gantries, four hangers and two grasping-wagons. On this landing-station can land three space-rockets in a few minutes intervals. The first and second landed space-rockets can be quick moved on hangers and be strong fasten by means of four rotating-wedges. The third landed space-rocket remains on both deck-gantries and is fastened by means of four rotating-poles which reach from two grasping-wagons. Presented here the ship with landing-station having strong fastening of the space-rockets enables sea-transportation even at stormy sea. Both deck-gantries are huge and can precisely and separably move along the entire ship. Before landing of every space-rocket, both deck-gantries are entirely spread apart in two opposite directions of this ship. In such arrangement both deck-gantries are ready and await landing of every space-rocket. Both deck-gantries can approach to each over and touch on themselves with the bumpers. Therefor short time before landing of each space-rocket, both deck-gantries approach to each over and together place themselves under the landing space-rocket. In order to accomplish it, each deck-gantry can move until direction of the opposite deck-gantry, if necessary during landing of some space-rocket. It causes that each space-rocket can land almost on entire length of the ship. While on drawings there are shown only landings examples in the ship center.

On both deck-gantries tops are installed four damping-wagons and two large damping-wagons. All damping-wagons can precisely roll transverse the ship on both deck-gantries tops. Short time before landing of each space-rocket, two damping-wagons place themselves under the landing space-rocket. It causes that each space-rocket can land almost on entire width of the ship. On two damping-wagons vertically lands one booster-space-rocket as hangs itself on its spreadable-arms. On next two damping-wagons lands also one booster-space-rocket. Whereas on two large damping-wagons vertically lands one main-space-rocket. After the space-rocket hanging itself, all damping-wagons can be in fullness squeezed down. Then two squeezed down damping-wagons can roll over from two deck-gantries tops onto two hangers tops. It is possible because constructions of the entire hangers and of the deck-gantries are entirely adapted with constructions and function of all damping-wagons. Each damping-wagon has four layers of several conic-springs in vertical setting which can be in fullness squeeze down. Therefor all damping-wagons have damping high range during hanging the space-rockets equipped with several spreadable-arms. Simultaneously all damping-wagons maintain unshaken and stable top surfaces during their squeezing down by the space-rocket.

Two space-rockets after landing can be quick moved from two deck-gantries to four hangers. Therefor in the landing-station are mounted four hangers this way that one par of hangers is mounted on each side of the ship. The hangers in construction reminds immovable towers. Each hanger has two rotating-wedges which serve for fastenings of one space-rocket. One par of hangers serve for hanging one space-rocket and fastening it by means of four rotating-wedges.

And in the landing-station are installed also two low build grasping-wagons each having two rotating-poles. Both grasping-wagons can move on both movable-decks transverse the ship. Moreover both grasping-wagons can together move in between one pair of hangers. Because both grasping-wagons are low build and are situated on both movable-decks thus they can move under every space-rocket which will hang itself on two damping-wagons on both deck-gantries. After each space-rocket landing, both grasping-wagons will move under this space-rocket bottom and will block its swinging bottom by means of four rotating-poles. Next two squeeze down damping-wagons with hanged space-rocket and both grasping-wagons having grasped this space-rocket bottom can move to ship side and between one pair of hangers. In order to perform it, both damping-wagons and both grasping-wagons must move at equal speeds toward one pair of hangers. After arriving all wagons between one pair of hangers, the hanged space-rocket will be fastened at bottom by means of four rotating-wedges off two hangers. Then it will be possible to loose pressure of four rotating-poles and lower them down. And next both grasping-wagons will be able to move under this hanged space-rocket toward the ship center that mean return on both movable-decks. Then the entire landing-station will be instantly ready for landing the next space-rocket. It will be enough to entirely spread apart both deck-gantries on ship two directions. Both grasping-wagons serve also for strong fastening of the last landed space-rocket bottom.

In this utter system more exact description of the ship design and its action is following. Thus this utter system comprises also an exceptional sea-going ship having deck-mounted landing-station. And this ship has several joined hulls, two horizontally movable-decks and two ballasting-wagons. The ship joined hulls construction consists of two long side-hulls and two short central-hulls which all are permanently fastened with four above-water copular-hulls.

Both horizontally movable-decks are huge and installed directly above all joined hulls. Both movable-decks can be quick and entirely spread apart in two directions of the ship in order to create inside this ship hull a jumbo abyss wherein there is only sea-water. Such spreading apart of these movable-decks may be necessary in order to prevent some strike of the space-rocket which failed to stop its descent down. Then this space-rocket will plunge into sea-water. This kind coincidence is shown for example on FIG. 274-275 and there one booster-space-rocket slips by through a wide-opened interior of the ship at open sea.

Two ballasting-wagons are installed inside the ship hull and are placed in two tunnels which are transverse to this ship hull. Both ballasting-wagons serve for very quick and precise ballasting the entire ship to perfectly horizontal position during landing each space-rocket and furthermore during moving each one on some hangers. Furthermore both ballasting-wagons serve also for automatic, continuous, quick and precise ballasting this ship during seafaring.

In this utter system more exact description of the harbor terminal design and its action is following. Thus, this utter system comprises also the harbor terminal which have two movable ground-gantries and one movable ground-crane for the space-rockets reloading. The movable ground-crane is a lot bigger than both ground-gantries. The ground-crane has some beams which reach up above the ship so that this ground-crane could lift one space-rocket and subsequently shift this space-rocket on both ground-gantries. The entire ground-crane will move backwards before the space-rockets liftoff. Both movable ground-gantries serve for three space-rockets lading after unloading from the ship. And later these two ground-gantries serve for three joined space-rockets launch preparation all time in vertical position thus during hanging on these two ground-gantries. And therefor all space-rockets can liftoff from two ground-gantries whilst these space-rockets vertically hang on their spreadable-arms. This even include that three joined space-rockets can liftoff this way. Both movable ground-gantries will spread apart on two sides immediately after the space-rockets liftoff. Summing-up, as result of this whole utter system with method of the space-rockets launches and their quick return to harbor terminal there is possible their very fast renewed launch, for example several hours after landing on ship.

The space-rocket liftoff from two ground-gantries creates also a few benefits like possibility of smooth igniting the main engines, smooth adjusting the space-rocket initial vertical position. Moreover it makes possible to abort the space-rocket liftoff plenty seconds after liftoff. It means after liftoff and some space-rocket failure to descend the whole space-rocket down and hang it back on two ground-gantries. It would be reverse process in comparison to the liftoff, thus like from FIG. 7 to FIG. 4.

Moreover this whole utter system makes possible aborting the space-rocket ascent any time after liftoff and next perform emergency landing of the whole space-rocket on ship. As result there is possible total salvage of the whole space-rocket together with mounted on top some modules and load.

BRIEF DESCRIPTION OF THE DRAWINGS— 275 NUMBERS

FIG. 1 is the side view and shows the space-rockets vertical landing method in the utter system for multiple use of several space-rockets equipped with several spreadable-arms 5. Here is shown the method of three space-rockets vertical landing on ship 10 with deck-mounted landing-station having four hangers 24, two grasping-wagons 44, two deck-gantries 20 with several damping-wagons 30 or 31 whereon each space-rocket vertically lands as hangs itself on its spreadable-arms 5. On landing-station can land three space-rockets in a few minutes intervals. Two first can be quick moved on hangers and fasten. The third landed space-rocket remains on both deck-gantries and is fastened by both grasping-wagons. Whereas FIG. 1 is the side view of the entire ship 10 which has deck-mounted the multi-part landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. The current view shows just vertically landing one booster-space-rocket 1 with entirely lifted upward (spread out) all spreadable-arms 5. This FIG. 1 shows additionally an enlarged fragment with the damping-wagon 30 and the second enlarged fragment of the booster-space-rocket 1 upper part showing the spreadable-arms 5 and a few steering flaps 6. Furthermore nearby to ship 10, current FIG. 1 shows the second booster-space-rocket 1 and the main-space-rocket 2 which both have also entirely lifted upward (spread out) all their spreadable-arms 5. This view shows and explains that on same ship 10 with such landing-station can still additionally vertically land these two earlier mentioned space-rockets.

FIG. 2 is the top view of the entire ship 10 in the same situation like on FIG. 1.

FIG. 3 is the front view of the entire ship 10 in the same situation like on FIG. 1.

FIG. 4 is the side view and shows the space-rockets launch method in the utter system for multiple use of several space-rockets equipped with several spreadable-arms 5. Here is shown the harbor terminal for three jointed space-rockets launch preparation, liftoff and later unloading from the ship 10. The harbor terminal comprises two movable ground-gantries 104 and one movable ground-crane 105. Therefor currently three joined space-rockets hang on all their spreadable-arms 5 on two ground-gantries 104 and will liftoff this way. These three joined space-rockets are one main-space-rocket 2 which is joined on both sides with two booster-space-rockets 1. On main-space-rocket 2 top it is mounted the assemblage which consist of the second-stage-rocket 3 with attached the sectional-load-cover 4. And on this FIG. 4 is also sketched the side drawing of one movable ground-crane 105, because it earlier moved away.

FIG. 5 is the top view of FIG. 4 in the same arrangement and situation.

FIG. 6 is the front view of FIG. 4 in the same arrangement and situation.

FIG. 7 is the side view of three joined space-rockets which are awhile after the liftoff and the side view of two ground-gantries 104 which are spread somewhat apart on two sides.

FIG. 8 is a prospectus presentation which shows many crowd scenes in the utter system for multiple use of several space-rockets equipped with several spreadable-arms 5. The current whole presentation shows the methods of three joined space-rockets launch and entire process ascent toward the Earth's orbit, descent and vertical landing with the return-load according to current invention. Therefor this FIG. 8 shows for example plurality drawing statuses of three joined space-rockets with their liftoff, joined ascent, their separation, further separated ascent toward the Earth's orbit, deploy the load, dock the return-load, and their individual descending and vertical landing aboard the ship 10 at open sea. On all space-rocket statuses and alongside the arrows show the directions of their traveling trajectories. These three joined space-rockets are the same like on previous FIG. 4, 5, 6, 7 and further FIG. 268, 269 and these are one main-space-rocket 2 which is joined on both sides with two booster-space-rockets 1. On main-space-rocket 2 top it is mounted the assemblage which consist of the second-stage-rocket 3 with attached the sectional-load-cover 4. At beginning these three space-rockets statuses are in two front drawings. Thereafter all space-rockets statuses are in the side drawings and show their travel toward the ship 10 which is in the side drawing as well. Here alongside the space-rocket drawing statuses are the numbers in some small circles which explain the space-rockets landing sequences. Descent process from the Earth's orbit individually by three space-rockets will end with vertical landing aboard the ship 10. Therefor both deck-gantries 20 are entirely spread apart in two directions before landing of every space-rocket like it is shown on current view. The entire prospectus presentation on FIG. 8 targets presentation that is possible individual, vertical landing as many as three space-rockets equipped with spreadable-arms 5 on one ship 10 at sea.

FIG. 9 is the top view and shows the space-rockets vertical unloading method in the utter system for multiple use of several space-rockets equipped with several spreadable-arms 5. Here is shown the method of three space-rockets vertical unloading from the ship 10 at harbor terminal according to current invention. Therefor this FIG. 9 shows the ship 10 which just moored at harbor terminal for unloading of three space-rockets which later can be launch again together or individually. This harbor terminal consists of two ground-gantries 104 and of one movable ground-crane 105. Aboard the ship 10 are hanged and still individually fastened three space-rockets.

FIG. 10 is the front view of FIG. 9 in the same arrangement and situation.

FIG. 11 is the side view of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. Therefor nearby the ship 10 is also one booster-space-rocket 1 which has entirely lifted upward (spread out) all spreadable-arms 5. The ship 10 and landing-station are ready for landing the first booster-space-rocket 1. The same side view of the entire ship 10 is also shown as enlarged on FIG. 270.

FIG. 12 is the top view of the entire ship 10 in the same arrangement and situation like on FIG. 11. The same top view of the entire ship 10 is also shown as enlarged on FIG. 271.

FIG. 13 is the front view of the entire ship 10 in the same arrangement and situation like on FIG. 11. The same front view of the entire ship 10 is also shown as enlarged on FIG. 272.

FIG. 14 is the side view of the entire ship 10 which has deck-mounted landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. This view shows this ship 10 and the landing-station ready for landing the second booster-space-rocket 1 because on her earlier already landed the first booster-space-rocket 1. Therefor here the ship 10 is with one booster-space-rocket 1 which hangs on two hangers 24 and is already fastened at bottom by means of four rotating-wedges 25.

FIG. 15 is the top view of the entire ship 10 in the same situation like on FIG. 14.

FIG. 16 is the front view of the entire ship 10 in the same situation like on FIG. 14.

FIG. 17 is the side view of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. This view shows this ship 10 and the landing-station ready for landing the third space-rocket because earlier already landed two booster-space-rockets 1. Therefor the current view shows the ship 10 with two booster-space-rockets 1 whereas each one hangs on two hangers 24 and each one is fastened at bottom by means of four rotating-wedges 25.

FIG. 18 is the top view of the entire ship 10 in the same situation like on FIG. 17.

FIG. 19 is the front view of the entire ship 10 in the same situation like on FIG. 17.

FIG. 20 is the side view of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. Here this ship 10 is with three individually hanged and fastened space-rockets and which are ready for transporting over sea for unloading at the harbor terminal.

FIG. 21 is the top view of the entire ship 10 in the same situation like on FIG. 20.

FIG. 22 is the front view of the entire ship 10 in the same situation like on FIG. 20.

FIG. 23 is the side view of the alone entire multi-part landing-station for individual, vertical landing of three space-rockets. This multi-part landing-station is in the same arrangement like aboard the ship 10 however the current view is without the grasping-wagons 44.

FIG. 24 is the top view of FIG. 23 in the same arrangement and situation.

FIG. 25 is the front view of FIG. 23 in the same arrangement and situation.

FIG. 26 is the side view of two whole deck-gantries 20 by themselves which are in the same arrangement like aboard the ship 10 and the same like on FIGS. 1-3 and 11-13.

FIG. 27 is the top view of two whole deck-gantries 20 in the same arrangement like on FIG. 26.

FIG. 28 is the front view of two whole deck-gantries 20 in the same arrangement like on FIG. 26.

FIG. 29 is the side view of two pairs of hangers 24 in the same arrangement like on ship 10.

FIG. 30 is the top view of two pairs of hangers 24 in the same arrangement like on FIG. 29.

FIG. 31 is the front view of two pairs of hangers 24 in the same arrangement like on FIG. 29.

FIG. 32 is the enlarged side view of one pair of hangers 24 wherein each has two rotating-wedges 25 lowered down and with the arrows showing their rotating directions.

FIG. 33 is the top view of FIG. 32 in the same arrangement.

FIG. 34 is the front view of FIG. 32 in the same arrangement.

FIG. 35 is the enlarged side view of one pair of hangers 24 with the space-rocket-tube 51 fragment which is fastened by means of four rotating-wedges 25.

FIG. 36 is the top view of FIG. 35 in the same arrangement.

FIG. 37 is the front view of FIG. 35 in the same arrangement.

FIG. 38 is the top view of the horizontal sectional view according to S-S line on FIG. 35.

FIG. 39 is the enlarged side view of one pair of hangers 24 whereon tops in the upper-short-rails 26 stand two damping-wagons 30.

FIG. 40 is the top view of FIG. 39 in the same arrangement.

FIG. 41 is the front view of FIG. 39 in the same arrangement.

FIG. 42 is the enlarged side view of one pair of hangers 24 with hanged and fastened one booster-space-rocket 1.

FIG. 43 is the top view of FIG. 42 in the same arrangement and situation.

FIG. 44 is the front view of FIG. 42 in the same arrangement and situation.

FIG. 45 is the enlarged side view of the rotating-wedges 25 with some hanger 24 fragments sketches which are performed with the dashed lines. All four rotating-wedges 25 are completely lowered down and with the arrows showing their rotating directions.

FIG. 46 is the top view of FIG. 45 in the same arrangement.

FIG. 47 is the front view of FIG. 45 in the same arrangement.

FIG. 48 is the enlarged side view of four rotating-wedges 25 which are rotated in such way that they all together tighten up the space-rocket-tube 51 fragment.

FIG. 49 is the top view of FIG. 48 in the same arrangement and situation.

FIG. 50 is the front view of FIG. 48 in the same arrangement and situation.

FIG. 51 is the top view and shows for example the space-rocket bottom that is moved away from correct location.

FIG. 52 is a lot enlarged side view of two rotating-wedges 25 which are wholly lowered down.

FIG. 53 is the top view of FIG. 52 in the same arrangement.

FIG. 54 is the front view of FIG. 52 in the same arrangement.

FIG. 55 is a lot enlarged side view of one pair of hangers 24 upper part in the same status like was earlier shown on FIG. 39. On hangers 24 tops and on upper-short-rails 26 stand two damping-wagons 30.

FIG. 56 is the top view of FIG. 55 in the same arrangement and situation.

FIG. 57 is the front view of FIG. 55 in the same arrangement and situation.

FIG. 58 is a lot enlarged side view of one pair of hangers 24 upper part in the same statuses like were earlier shown on FIG. 42. Here on one pair of hangers 24 is hanged one booster-space-rocket 1.

FIG. 59 is the top view of FIG. 58 in the same arrangement and situation.

FIG. 60 is the front view of FIG. 58 in the same arrangement and situation.

FIG. 61 is a lot enlarged side view of two damping-wagons 30 which are not squeezed down and they stand on upper-short-rails 26 which are on tops of one pair of hangers 24.

FIG. 62 is the top view of FIG. 61 in the same arrangement and situation.

FIG. 63 is the front view of FIG. 61 in the same arrangement and situation.

FIG. 64 is a lot enlarged side view of two damping-wagons 30 which for example are squeezed down and stand on upper-short-rails 26 which are on tops of one pair of hangers 24.

FIG. 65 is the top view of FIG. 64 in the same arrangement and situation.

FIG. 66 is the front view of FIG. 64 in the same arrangement and situation.

FIG. 67 is a lot enlarged side view of one entire damping-wagon 30 which is not squeezed down and in different manner than previously, stands on two upper-long-rails 23 which are on one deck-gantry 20 top.

FIG. 68 is the top view of FIG. 67 in the same arrangement and situation.

FIG. 69 is the front view of FIG. 67 in the same arrangement and situation.

FIG. 70 is the bottom projection of FIG. 67 in the same arrangement and situation.

FIG. 71 is the top view of the horizontal sectional view according to S-S line on FIG. 69.

FIG. 72 is a lot enlarged side view of one entire damping-wagon 30 and which for example is squeezed down and does not stand on any rails.

FIG. 73 is the top view of FIG. 72 in the same arrangement.

FIG. 74 is the front view of FIG. 72 in the same arrangement.

FIG. 75 is a lot enlarged side view of one large damping-wagon 31 which is not squeezed down and stands on two upper-long-rails 23 which are on one deck-gantry 20 top.

FIG. 76 is the top view of FIG. 75 in the same arrangement and situation.

FIG. 77 is the front view of FIG. 75 in the same arrangement and situation.

FIG. 78 is the bottom projection of FIG. 75 in the same arrangement and situation.

FIG. 79 is the top view of the horizontal sectional view according to S-S line on FIG. 75.

FIG. 80 is the side view of two grasping-wagons 44 wherein each with two rotating-poles 45. Both grasping-wagons 44 stand on four short-transverse-rails 48. The rotating-poles 45 are lifted upward.

FIG. 81 is the top view of FIG. 80 in the same arrangement and situation.

FIG. 82 is the front view of FIG. 80 in the same arrangement and situation.

FIG. 83 is the side view of two grasping-wagons 44 standing on four long-transverse-rails 47. Both grasping-wagons 44 by means of four rotating-poles 45 tighten one main-space-rocket 2 bottom.

FIG. 84 is the top view of FIG. 83 in the same arrangement and situation.

FIG. 85 is the front view of FIG. 83 in the same arrangement and situation.

FIG. 86A is the side view of one booster-space-rocket 1 upper part which has six spreadable-arms 5 and four steering flaps 6. Here all spreadable-arms 5 are entirely lowered down. Whereat all four flaps 6 are vertically set and are entirely inside the space-rocket fuselage.

FIG. 86B is the side view of one booster-space-rocket 1 bottom part which has one sliding-engines-cover 7 and which currently is entirely lifted upward.

FIG. 87 is the top view of FIG. 86A, B in two equal views which are rotated 90 degrees.

FIG. 88A is the front view of FIG. 86A in the same arrangement and situation.

FIG. 88B is the front view of FIG. 86B in the same arrangement and situation.

FIG. 89A is the side view of one booster-space-rocket 1 upper part which has a little lifted upward all six spreadable-arms 5. Whereat all four flaps 6 are a lot deflected out.

FIG. 89B is the side view of one booster-space-rocket 1 bottom part which has one sliding-engines-cover 7 and which is entirely lifted upward.

FIG. 90 is the top view of FIG. 89A, B in the same arrangement and situation.

FIG. 91A is the side view of one booster-space-rocket 1 upper part which has entirely lifted upward (spread out) all six spreadable-arms 5. And whereat all four flaps 6 are entirely deflected out.

FIG. 91B is the side view of one booster-space-rocket 1 bottom part which has one sliding-engines-cover 7 and which currently is entirely lifted upward.

FIG. 92 is the top view of FIGS. 91A, B and 93A, B in the same arrangement and situation. This FIG. 92 is the top view in two equal views which are rotated 90 degrees.

FIG. 93A is the front view of FIG. 91A in the same arrangement and situation.

FIG. 93B is the front view of FIG. 91B in the same arrangement and situation.

FIG. 94A is the side view of one main-space-rocket 2 upper part which has all spreadable-arms 5 entirely lowered down. And all four flaps 6 are vertically set and are inside the space-rocket fuselage.

FIG. 94B is the side view of one main-space-rocket 2 bottom part which has one sliding-engines-cover 7 and which currently is entirely lifted upward.

FIG. 95 is the top view of FIG. 94A, B and FIG. 96A, B in the same arrangement and situation. This FIG. 95 is the top view in two equal views which are rotated 90 degrees.

FIG. 96A is the front view of FIG. 94A in the same arrangement and situation.

FIG. 96B is the front view of FIG. 94B in the same arrangement and situation.

FIG. 97A, B are the side views of one main-space-rocket 2 upper and bottom parts which has entirely lifted upward (spread out) all ten spreadable-arms 5. Whereat all four flaps 6 are entirely deflected out. Whereat the sliding-engines-cover 7 is entirely lifted upward.

FIG. 98 is the top view of FIG. 97A, B in the same arrangement and situation. This FIG. 98 is the top view in two equal views which are rotated 90.

FIG. 99A, B is the front view of FIG. 97A, B in the same arrangement and situation.

FIG. 100 is the side view of one booster-space-rocket 1 upper part and of two deck-gantries 20 upper part whereon tops stand two damping-wagons 30 and which are not squeezed down. This view shows just vertically landing the booster-space-rocket 1 which in a moment will hang itself on two damping-wagons 30.

FIG. 101 is the top view of FIG. 100 in the same arrangement and situation.

FIG. 102 is the side view of one main-space-rocket 2 upper part and of two deck-gantries 20 upper part whereon tops stand two large damping-wagons 31 and which are not squeezed down. This view shows just vertically landing main-space-rocket 2 which in a moment will hang itself on two large damping-wagons 31.

FIG. 103 is the top view of FIG. 102 in the same arrangement and situation.

FIG. 104 is the side view of four steering flaps 6 installed in the main-space-rocket 2 upper part. Currently all four flaps 6 are vertically set and are entirely inside the space-rocket fuselage.

FIG. 105 is the top view of FIG. 104 in the same arrangement.

FIG. 106 is the front view of FIG. 104 in the same arrangement.

FIG. 107 is the side view of four steering flaps 6 in the main-space-rocket 2 upper part. Currently all four flaps 6 are a lot deflected outside.

FIG. 108 is the top view of FIG. 107 in the same arrangement.

FIG. 109 is the front view of FIG. 107 in the same arrangement.

FIG. 110 is the side view of four steering flaps 6 in the main-space-rocket 2 upper part. Currently all four flaps 6 are entirely deflected outside

FIG. 111 is the top view of FIG. 110 in the same arrangement.

FIG. 112 is the front view of FIG. 110 in the same arrangement.

FIG. 113 is the enlarged side view of one steering flap 6 with the sketches of its deflection mechanism in the main-space-rocket 2 fragment. Currently this flap 6 is vertically set and entirely inside the space-rocket fuselage.

FIG. 114 is the top view of FIG. 113 in the same arrangement.

FIG. 115 is the front view of FIG. 113 in the same arrangement.

FIG. 116 is the enlarged side view of one steering flap 6 with the sketches of its deflection mechanism in the main-space-rocket 2 fragment. Currently this flap 6 is entirely deflected outside the space-rocket fuselage.

FIG. 117 is the top view of FIG. 116 in the same arrangement.

FIG. 118 is the front view of FIG. 116 in the same arrangement.

FIG. 119 is the side view of the fragment of one main-space-rocket 2 upper part which has entirely lowered down all ten spreadable-arms 5. Here is visible in which way are spaced out all ten spreadable-arms 5 outside the space-rocket fuselage.

FIG. 120 is the top view of FIG. 119 in the same arrangement. FIG. 120 shows all mechanisms outside and inside space-rocket and in which way are spaced out all ten spreadable-arms 5. This FIG. 120 is the top view in two equal views which are rotated 90 degrees.

FIG. 121 is the front view of FIG. 119 in the same arrangement.

FIG. 122 is the side view of the fragment of one main-space-rocket 2 upper part which has entirely lifted upward all ten spreadable-arms 5 and consequently they are completely spread out on two sides. And therefor these spreadable-arms 5 are transverse the space-rocket fuselage.

FIG. 123 is the top view of FIG. 122 in the same arrangement. FIG. 123 shows all mechanisms outside and inside space-rocket and in which way are spaced out all ten spreadable-arms 5.

FIG. 124 is the enlarged side view of the fragment of one booster-space-rocket 1 upper part which has entirely lifted upward all six spreadable-arms 5 and consequently they are completely spread out on two sides and are transverse the space-rocket fuselage.

FIG. 125 is the top view of FIG. 124 in the same setting. This FIG. 125 shows all mechanisms outside and inside space-rocket and in which way are spaced out all six spreadable-arms 5.

FIG. 126 is the side view of one entire spreadable-arm 5 together with its moving mechanism and with one blocking-bar 54 and its pushing mechanism. This entire spreadable-arm 5 is entirely lowered down to P1 first setting. Whilst the blocking-bar 54 is inside the space-rocket fuselage. This FIG. 126 is the side view with the partial vertical sectional view.

FIG. 127 is the top view of FIG. 126 in the same arrangement. This FIG. 127 is the top view in two equal views which are rotated 90 degrees.

FIG. 128 is the front view of FIG. 126 in the same arrangement. This FIG. 128 is the front view but only of the sub-assemblies outside the space-rocket.

FIG. 129 is the enlarged side view of the FIG. 126 fragment. Here are one spreadable-arm 5 fragment with its moving mechanism and one blocking-bar 54 with its pushing mechanism.

FIG. 130 is the enlarged top view of FIG. 127 in the same arrangement. This FIG. 130 is the top view in two equal views which are rotated 90 degrees.

FIG. 131 is the enlarged front view of FIG. 128 in the same arrangement.

FIG. 132 is the very enlarged side view of the fragment of previous FIG. 129. It shows in the most detail way the entire moving mechanism construction of the spreadable-arm 5 in the space-rocket fuselage fragment.

FIG. 133 is the very enlarged top view of FIG. 130 in the same arrangement.

FIG. 134 is the very enlarged front view of FIG. 131 in the same arrangement.

FIG. 135 is the enlarged side view of the alone entire moving mechanism of spreadable-arm 5 together with the fragments of two lateral-beams 56 which all are in P1 setting.

FIG. 136 is the top view of FIG. 135 in the same arrangement.

FIG. 137 is the front view of FIG. 135 in the same arrangement.

FIG. 138 is the enlarged side view of one alone moving mechanism components of one spreadable-arm 5.

FIG. 139 is the top view of FIG. 138 in the same arrangement.

FIG. 140 is the front view of FIG. 138 in the same arrangement.

FIG. 141 is the enlarged side view of four flat-bars 72 (having oval-openings) which are permanently fastened to both lateral-beams 56 upper bent parts.

FIG. 142 is the top view of FIG. 141 in the same arrangement.

FIG. 143 is the front view of FIG. 141 in the same arrangement.

FIG. 144 is the side view and the partial vertical sectional view which outside and partly inside the space-rocket fragment shows one entire spreadable-arm 5 in P2 setting which is in one-quarter lifted upward and consequently protrudes outside the space-rocket fuselage. On this FIG. 144 are also sketched intermediate settings of spreadable-arm 5, it means in P3, P4 and P5 settings. There is also marked P6 final setting ergo whilst the spreadable-arm 5 is entirely lifted upward.

FIG. 145 is the top view of FIG. 144 in the same arrangement and situation.

FIG. 146 is the front view of FIG. 144 in the same arrangement and situation. This FIG. 146 is the front view but only of the sub-assemblies outside the space-rocket.

FIG. 147 is the side view of the enlarged fragment of FIG. 144. The current view shows the upper part of spreadable-arm 5 in P2 setting.

FIG. 148 is the top view of FIG. 147 in the same arrangement.

FIG. 149 is the front view of FIG. 147 in the same arrangement.

FIG. 150 is the side view and the partial vertical sectional view of the space-rocket fuselage. And shows outside and inside the space-rocket fragment the side view of one entire spreadable-arm 5 in the P6 setting which is entirely lifted upward and consequently it is transverse the space-rocket fuselage. Whereat the blocking-bar 54 is slid maximally outside the space-rocket fuselage and it entirely blocked the middle-beam 55 in the spreadable-arm 5.

FIG. 151 is the top view of FIG. 150 in the same arrangement.

FIG. 152 is the front view of FIG. 150 in the same arrangement.

FIG. 153 is the auxiliary side view and partial vertical sectional view that shows FIG. 152 only in the middle.

FIG. 154 is the side view of the enlarged fragment of FIG. 150.

FIG. 155 is the top view of FIG. 154 in the same arrangement.

FIG. 156 is the front view of FIG. 154 in the same arrangement.

FIG. 157 is the auxiliary side view and partial vertical sectional view that shows FIG. 156 only in the middle.

FIG. 158 is the side view of alone spreadable-arm 5 which is entirely lowered down ergo it is in P1 setting. It shows that each spreadable-arm 5 mainly consists of two lateral-beams 56 and of one middle-beam 55.

FIG. 159 is the top view of FIG. 158 in the same arrangement.

FIG. 160 is the front view of FIG. 158 in the same arrangement.

FIG. 161 is the side view of the enlarged fragments of FIG. 158 in the same arrangement.

FIG. 162 is the top view of FIG. 161 in the same arrangement.

FIG. 163 is the front view of FIG. 161 in the same arrangement.

FIG. 164 is the side view of the alone spreadable-arm 5 which is in one-quarter lifted upward to P2 setting.

FIG. 165 is the top view of FIG. 164 in the same arrangement.

FIG. 166 is the front view of FIG. 164 in the same arrangement.

FIG. 167 is the side view of the enlarged fragments of FIG. 164 in the same arrangement.

FIG. 168 is the top view of FIG. 167 in the same arrangement.

FIG. 169 is the front view of FIG. 167 in the same arrangement.

FIG. 170 is the side view of the alone spreadable-arm 5 together with the entire pushing mechanism of the blocking-bar 54 which is not slid outside. The spreadable-arm 5 is entirely lifted upward to P6 setting.

FIG. 171 is the top view of FIG. 170 in the same arrangement.

FIG. 172 is the front view of FIG. 170 in the same arrangement.

FIG. 173 is the side view of the alone middle-beam 55 together with entire pushing mechanism of the blocking-bar 54 which is not slid outside.

FIG. 174 is the top view of FIG. 173 in the same arrangement.

FIG. 175 is the front view of FIG. 173 in the same arrangement.

FIG. 176 is the side view of the alone middle-beam 55 together with the entire pushing mechanism of the blocking-bar 54 which is slid very little outside.

FIG. 177 is the side view of the alone middle-beam 55 together with the entire pushing mechanism of the blocking-bar 54 which is slid a lot outside.

FIG. 178 is the side view of the alone spreadable-arm 5 together with the entire pushing mechanism of the blocking-bar 54 which is maximally slid outside.

FIG. 179 is the top view of FIG. 178 in the same arrangement.

FIG. 180 is the side view of the enlarged fragments of FIG. 170 in the same arrangement.

FIG. 181 is the top view of FIG. 180 in the same arrangement.

FIG. 182 is the front view of FIG. 180 in the same arrangement.

FIG. 183 is the side view of the enlarged fragments of FIG. 173 in the same arrangement.

FIG. 184 is the top view of FIG. 183 in the same arrangement.

FIG. 185 is the front view of FIG. 183 in the same arrangement.

FIG. 186 is the side view of the enlarged fragments of FIG. 176 in the same arrangement.

FIG. 187 is the top view of FIG. 186 in the same arrangement.

FIG. 188 is the side view of the middle-beam 55 bottom with inside visible the frictional-brake 68 sketches. Here this middle-beam 55 is vertically set ergo it is in P1 setting.

FIG. 189 is the top view of FIG. 188 in the same arrangement.

FIG. 190 is the front view of FIG. 188 in the same arrangement.

FIG. 191 is side view of the alone middle-beam 55 bottom with inside visible the frictional-brake 68 sketches. Here this middle-beam 55 is slanted to P6 full setting.

FIG. 192 is the side view of one sliding-engines-cover 7 which can be lowered down and which is flat underneath after lowering down. It is installed to a space-rocket fuselage bottom. Now this sliding-engines-cover 7 is entirely lifted upward and it causes that the main engines all nozzles 85 are entirely uncovered.

FIG. 193 is the top view of FIG. 192 in the same arrangement.

FIG. 194 is the front view of FIG. 192 in the same arrangement.

FIG. 195 is the bottom projection of FIG. 192 and that mean of the current space-rocket bottom in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the above views.

FIG. 196 is the side view of one sliding-engines-cover 7 which can be lowered down and which is flat underneath after lowering down. Currently this sliding-engines-cover 7 is entirely lowered down and it causes that the space-rocket bottom is entirely covered underneath and almost entirely at both sides.

FIG. 197 is the top view of FIG. 196 in the same arrangement and situation.

FIG. 198 is the front view of FIG. 196 in the same arrangement and situation.

FIG. 199 is the bottom projection of FIG. 196 and that mean of the current space-rocket bottom in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the above views. On these projections are visible that both jalousies 88 came to each other and touched on themselves in the U-form-rails 87 bottom and in their middle.

FIG. 200 is the side view of the sliding-engines-cover 7 which can be lowered down and which is flat underneath after lowering down. Currently the sliding-engines-cover 7 is entirely lifted upward and the exhaust-fumes 9 gush down of the main engines all nozzles 85.

FIG. 201 is the front view of FIG. 200 in the same arrangement.

FIG. 202 is the side view of the sliding-engines-cover 7 which can be lowered down and which is flat underneath after lowering down. Currently the sliding-engines-cover 7 is entirely lowered down and it causes that the space-rocket bottom is entirely covered.

FIG. 203 is the front view of FIG. 202 in the same arrangement.

FIG. 204 is the side view of one sliding-engines-cover 8 which can be lowered down and which is wedge-shaped underneath after lowering down. This sliding-engines-cover 8 is installed to the space-rocket fuselage bottom. Currently the sliding-engines-cover 8 is entirely lifted upward and it causes that all main-engines nozzles 85 are entirely uncovered. And currently the exhaust-fumes 9 gush down of the main engines all nozzles 85.

FIG. 205 is the top view of FIG. 204 in the same arrangement and situation.

FIG. 206 is the front view of FIG. 204 in the same arrangement and situation.

FIG. 207 is the bottom projection of FIG. 204 thus of current space-rocket bottom in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the above views.

FIG. 208 is the side view of the sliding-engines-cover 8 which can be lowered down and which is wedge-shaped underneath after lowering down. Here the sliding-engines-cover 8 is entirely lowered down and it causes that the space-rocket bottom is entirely covered. This view shows some main components emplacement of the sliding-engines-cover 8 in relation to themselves and with the components sketches which are veiled by some other members.

FIG. 209 is the front view of FIG. 208 in the same arrangement.

FIG. 210 is the side view of the sliding-engines-cover 8 which can be lowered down and which is wedge-shaped underneath after lowering down. Here the sliding-engines-cover 8 is also entirely lowered down and it causes that the space-rocket bottom is entirely covered. This view shows in what way this sliding-engines-cover 8 expands and divides in two sides some atmospheric air during the space-rocket descent.

FIG. 211 is the front view of FIG. 210 in the same arrangement and situation.

FIG. 212A, B is the side view of the upper and bottom parts of one booster-space-rocket 1 which descends in the first time period at giant speed in the Earth's atmosphere. Currently all six spreadable-arms 5 are entirely lowered down; four flaps 6 are a little deflected out; all six blocking-bars 54 are entirely slid outside; the sliding-engines-cover 7 is entirely lowered down.

FIG. 213 is the top view of FIG. 212A, B in the same situation. The FIG. 213 is in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views.

FIG. 214A, B is the front view of FIG. 212A, B in the same arrangement and situation.

FIG. 215A, B is the side view of the upper and bottom parts of one booster-space-rocket 1 which descends at average speed in the Earth's atmosphere. Currently all six spreadable-arms 5 are lifted somewhat upward; four flaps 6 are a lot deflected out; the sliding-engines-cover 7 is entirely lowered down.

FIG. 216 is the top view of FIG. 215A, B in the same arrangement and situation.

FIG. 217 is the side view of one entire main-space-rocket 2 that has revolvingly installed the sectional-load-cover 4 which is dividable into two sections and gradually foldable out on two opposite sides. This sectional-load-cover 4 is revolvingly installed to main-space-rocket 2 by means of four long cog-beams 93. Currently to main-space-rocket 2 is also directly attached the second-stage-rocket 3. The sectional-load-cover 4 is shut up and all cog-beams 93 are outside and on both sides of the second-stage-rocket 3.

FIG. 218 is the front view of FIG. 217 in the same arrangement and situation.

FIG. 219 is the side view which is the same like FIG. 217 albeit contains the load 100 sketches inside the shut up sectional-load-cover 4 and the second-stage-rocket 3 sub-assemblies sketches which are veiled by some other modules.

FIG. 220 is the front view of FIG. 219 in the same arrangement and situation.

FIG. 221 is the side view of the second-stage-rocket 3 whereon is attached the load 100.

FIG. 222 is the side view of the second-stage-rocket 3 where-from ascends away the load 100.

FIG. 223 is the enlarged side view of the main-space-rocket 2 upper part earlier shown on FIG. 219. This view shows the main-space-rocket 2 upper part which has revolvingly installed the sectional-load-cover 4 which is dividable into two sections and gradually foldable out on two opposite sides. Now the sectional-load-cover 4 is shut up. Whilst, inside the sectional-load-cover 4 is placed the load 100 which will be carried out on Earth's orbit.

FIG. 224 is the front view of FIG. 223 in the same arrangement and situation.

FIG. 225 is the enlarged side view of the main-space-rocket 2 upper part shown also earlier on similar

FIG. 223. Currently the sectional-load-cover 4 is lifted maximally upward on four cog-beams 93. This enables spreading it out on two sides.

FIG. 226 is the front view of FIG. 225 in the same arrangement and situation.

FIG. 227 is enlarged side view of the main-space-rocket 2 upper part shown earlier on similar FIG. 223, 225. Here the sectional-load-cover 4 is already spread a little out on two sides. Now, the load 100 is a lot uncovered.

FIG. 228 is significantly diminished the side view of one entire main-space-rocket 2 which has entirely folded out on two sides the sectional-load-cover 4 and shows the sketch its intermediate folding out.

FIG. 229 is the side view of the main-space-rocket 2 upper part which has entirely folded out on two sides the sectional-load-cover 4 and the sketch its intermediate folding out. Because of total folding out on two sides the sectional-load-cover 4, there is entirely uncovered the load 100 which is attached to second-stage-rocket 3.

FIG. 230 is the side view of the main-space-rocket 2 upper part which has also entirely folded out on two sides the sectional-load-cover 4. And here the second-stage-rocket 3 with attached load 100 ascend together upward because they already separated from the main-space-rocket 2.

FIG. 231 is the side view of the main-space-rocket 2 upper part which has entirely folded out on two sides the sectional-load-cover 4. Here the second-stage-rocket 3 with attached return-load 106 approaches to main-space-rocket 2 in order to dock with it.

FIG. 232 is the side view of the main-space-rocket 2 upper part whereto is already docked the second-stage-rocket 3 with attached return-load 106. Here the sectional-load-cover 4 is already a little shut up.

FIG. 233 is the side view of the alone main-space-rocket 2 upper part which has entirely folded out on two sides the sectional-load-cover 4.

FIG. 234 is the top view of the alone main-space-rocket 2 upper part which has entirely folded out on two sides the sectional-load-cover 4.

FIG. 235 is the side view of the main-space-rocket 2 upper part with a little shut up the sectional-load-cover 4.

FIG. 236 is the side view of the main-space-rocket 2 upper part with more shut up the sectional-load-cover 4.

FIG. 237 is the side view of the main-space-rocket 2 upper part, near to shutting up the sectional-load-cover 4.

FIG. 238 is the side view of the main-space-rocket 2 upper part which has the sectional-load-cover 4 entirely shut up. This sectional-load-cover 4 is maximally distant upward from the main-space-rocket 2 because it is held up by means of four long cog-beams 93.

FIG. 239 is the front view of FIG. 238 in the same arrangement and situation.

FIG. 240 is the side view of the main-space-rocket 2 upper part which has also the entirely shut up sectional-load-cover 4 which is already a lot lowered down on four cog-beams 93.

FIG. 241 is the front view of FIG. 240 in the same arrangement and situation.

FIG. 242 is the side view of the main-space-rocket 2 upper part which has also the entirely shut up sectional-load-cover 4 which is already entirely lowered down on four cog-beams 93. Therefore this sectional-load-cover 4 touched on with the main-space-rocket 2 fuselage.

FIG. 243 is the front view of FIG. 242 in the same arrangement and situation.

FIG. 244 is the enlarged side view of the entirely shut up sectional-load-cover 4 that is attached to main-space-rocket 2 upper part. Here is visible in what way are installed four hoisting-gears 96 of the sectional-load-cover 4 and four rotating-heads 94 of four cog-beams 93.

FIG. 245 is the top view of the horizontal sectional view according to S1-S1 line on FIG. 244.

FIG. 246 is the top view of the horizontal sectional view according to S2-S2 line on FIG. 247.

FIG. 247 is the front view of FIG. 244 in the same arrangement and situation.

FIG. 248 is the enlarged side view of the fragment of the entirely shut up sectional-load-cover 4 that is a little lifted up on four cog-beams 93 and therefor a little protrude from the main-space-rocket 2.

FIG. 249 is the front view of FIG. 248 in the same arrangement and situation.

FIG. 250 is the very plenty enlarged and detailed side view of two hoisting-gears 96 in the fragment of the entirely shut up sectional-load-cover 4 which is lifted upward.

FIG. 251 is the top view of FIG. 250 in the same arrangement and situation.

FIG. 252 is the front view of FIG. 250 in the same arrangement and situation.

FIG. 253 is the very plenty enlarged and detailed side view of two rotating-heads 94 of the cog-beams 93 in the fragment of the main-space-rocket 2 fuselage.

FIG. 254 is the top view of FIG. 253 in the same arrangement and situation.

FIG. 255 is the front view of FIG. 253 in the same arrangement and situation.

FIG. 256 is the side view of attaching variant wherein on main-space-rocket 2 top is mounted the assemblage and which consist of the second-stage-rocket 3 whereon is attached the load-module 103 and whereto is attached the crew-module 102.

FIG. 257 is the front view of FIG. 256 in the same arrangement and situation.

FIG. 258 is the side view of the attaching variant wherein on main-space-rocket 2 top is mounted the assemblage which only consists of the load-module 103 with the crew-module 102.

FIG. 259 is the front view of FIG. 258 in the same arrangement and situation.

FIG. 260 is the side view of the separated assemblage that consist of the second-stage-rocket 3 with attached load-module 103 whereto is attached the crew-module 102.

FIG. 261 is the side view of the alone crew-module 102.

FIG. 262 is the side view of example of one booster-space-rocket 1 descending in the atmosphere. This booster-space-rocket 1 has entirely lifted upward (spread out) its all six spreadable-arms 5.

FIG. 263 is the top view of FIG. 262 in the same arrangement and situation.

FIG. 264 is the side view of example of one main-space-rocket 2 descending in the atmosphere. This main-space-rocket 2 has entirely lifted upward (spread out) its all ten spreadable-arms 5. And this main-space-rocket 2 has on its top directly installed the sectional-load-cover 4.

FIG. 265 is the top view of FIG. 264 in the same arrangement and situation.

FIG. 266 is the side view of example of one main-space-rocket 2 descending in the atmosphere. This main-space-rocket 2 has also entirely lifted upward (spread out) all ten spreadable-arms 5. This view shows the attaching variant wherein on main-space-rocket 2 top is mounted the assemblage which consist of the second-stage-rocket 3 and the sectional-load-cover 4.

FIG. 267 is the side view of example of one main-space-rocket 2 descending in the atmosphere. This main-space-rocket 2 has also entirely lifted upward (spread out) all ten spreadable-arms 5. This view shows the attaching variant wherein on main-space-rocket 2 top is mounted the assemblage that consist of the second-stage-rocket 3 with attached load-module 103 and crew-module 102.

FIG. 268 is the diminished front view of three joined space-rockets. They are one main-space-rocket 2 that is joined on both sides with two booster-space-rockets 1. On main-space-rocket 2 top is mounted the assemblage that consist of the second-stage-rocket 3 and the sectional-load-cover 4.

FIG. 269 is the enlarged front view of the upper parts of three joined space-rockets which are on FIG. 268.

FIG. 270 is the enlarged side view of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. This view is the same like FIG. 11 albeit is enlarged. This view shows the ship 10 and the landing-station ready for landing the first booster-space-rocket 1 and alongside very such space-rocket.

FIG. 271 is the enlarged top view of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. This view is the same like FIG. 12 albeit is enlarged. This view shows this ship 10 and the landing-station ready for landing the first booster-space-rocket 1 and alongside very such space-rocket.

FIG. 272 is the enlarged front view of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. This view is the same like FIG. 13 albeit is enlarged. This view shows this ship 10 and the landing-station ready for landing the first booster-space-rocket 1 and alongside very such space-rocket.

FIG. 273 is prospectus presentation which shows for example several drawing statuses of one main-space-rocket 2 which lifted-off and its further traveling trajectory whilst unexpectedly happened failure of some main engine. The whole presentation shows process of this entire space-rocket salvation and its emergency landing aboard the ship 10 at open sea. This view targets display that each space-rocket equipped with spreadable-arms 5 can in emergency land aboard the ship 10.

FIG. 274 is the side view which shows for example one booster-space-rocket 1 which slips by through the wide-opened interior of the ship 10 at open sea. According to plan, this booster-space-rocket 1 was supposed to land on this ship 10. However during this space-rocket descent happened some failure of the main engines which were supposed to bring total stop of the space-rocket descent and make possible landing aboard the ship 10. In order to prevent any strike of this space-rocket onto ship 10 there were quick and entirely spread apart in two directions both movable-decks 15.

FIG. 275 is the top view of FIG. 274 in the same situation.

DISCLOSURE and DETAILED DESCRIPTION OF THE INVENTION AND DRAWINGS

The views on FIG. 1, 2, 3 show space-rockets vertical landing method in the utter system for multiple use of several space-rockets equipped with several spreadable-arms 5. Here is shown the method of three space-rockets vertical landing on ship 10 with deck-mounted landing-station having four hangers 24, two grasping-wagons 44, two deck-gantries 20 with several damping-wagons 30 or 31 whereon each space-rocket vertically lands as hangs itself on its spreadable-arms 5. On current landing-station can land three space-rockets in a few minutes intervals. Two first can be quick moved on hangers and fasten. The third landed space-rocket can remains on both deck-gantries and is fastened by both grasping-wagons. As result each space-rocket landing is super safe. This utter system is completely connected with utilization of several spreadable-arms 5 mounted on all space-rockets. Therefor the spreadable-arms 5 are the main characteristic feature of this utter system. More information about these spreadable-arms 5 is in description of further FIG. 86-88. Moreover in this utter system, each space-rocket (equipped with several spreadable-arms 5) can vertically land with some attached modules and return-load and this feature is super important possibility and advantage. Therefor this utter system includes that all space-rockets and their sub-assemblies and modules are designed and destined for multiple use thus return with the space-rockets on Earth. Consequently here presented the utter system for multiple use of suchlike space-rockets regard vertical landing as very important purpose of this here invention. Whereas here FIG. 1 is the side view, FIG. 2 is the top view, FIG. 3 is the front view. Current FIG. 1, 2, 3 show three views of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and fastening of three space-rockets equipped with several spreadable-arms 5. And therefor here FIG. 1, 2, 3 show just vertically landing one booster-space-rocket 1 with entirely lifted upward (spread out) all spreadable-arms 5. Near to ship 10, FIG. 1 shows also the second booster-space-rocket 1 and the main-space-rocket 2 which both have entirely lifted upward (spread out) their all spreadable-arms 5. All views show and explain that on same ship 10 with such landing-station can still additionally vertically land these two earlier mentioned space-rockets. Moreover all these landings can progress in a few minutes intervals. And FIG. 1 shows additionally an enlarged fragment with one damping-wagon 30 and the second enlarged fragment with the booster-space-rocket 1 upper part showing the spreadable-arms 5 and the steering flaps 6. All current views show just vertically landing one booster-space-rocket 1 and therefor from this space-rocket all main engines gush exhaust-fumes 9. This vertically landing booster-space-rocket 1 will soon hang up on two damping-wagons 30 which stand on two deck-gantries 20 tops. This two damping-wagons 30 stand almost in centers of both deck-gantries 20 tops. Whereat both deck-gantries 20 approached near to each other in the ship 10 center. Because the ship 10 has the landing-station, the first and second landed space-rockets can be quick moved on hangers 24 and be strong fasten by means of four rotating-wedges 25. The third so the last landed space-rocket will remain on both deck-gantries 20 and will be fasten by means of four rotating-poles 45 which reach from two grasping-wagons 44. Presented here the ship 10 with landing-station having strong fastening of the space-rockets enables sea-transportation even at stormy sea. Simultaneously, all mentioned feature are very important possibilities and advantages of this utter system. Therefor current views on FIG. 1, 2, 3 show entire multi-part landing-station construction which consists of four hangers 24 with several rotating-wedges 25, two huge movable deck-gantries 20 whereon tops are installed four damping-wagons 30 and two large damping-wagons 31, two low build grasping-wagons 44 with some rotating-poles 45. Here is visible that the upper-short-rails 26 on all hangers 24 tops fit to upper-long-rails 23 on both deck-gantries 20 tops whilst these both deck-gantries 20 stand at ship 10 center. This utter system comprises also that the ship 10 has several joined hulls, two movable-decks 15 and two ballasting-wagons 18. The ship 10 has exceptional construction and is designed like sea-going-ship. The views on FIG. 1, 2, 3 show the entire ship 10 joined hulls construction which consists of two long side-hulls 11 and two short central-hulls 12. All these mentioned hulls are permanently fastened with four above-water copular-hulls 13. On each long side-hull 11 surface is a main-board 14.

The ship 10 has also two huge horizontally movable-decks 15 which are installed directly above all joined hulls and can move on both main-boards 14. Both movable-decks 15 can be quick and entirely spread apart in two directions of the ship 10 in order to create inside this ship hull the jumbo abyss wherein there is only sea-water. More information about these horizontally movable-decks 15 is in description of further FIG. 11-13 and in FIG. 274-275.

Inside joined hulls construction the ship 10 has installed two ballasting-wagons 18. These two ballasting-wagons 18 are placed in two tunnels 17 which are transverse to ship 10 hull. And in these two tunnels 17, both ballasting-wagons 18 are currently shifted into such side-setting which maintains exactly horizontal position of this ship 10. Both ballasting-wagons 18 serve for very quick and precise ballasting the entire ship to perfectly horizontal position. Furthermore FIG. 1-3 show some sophisticated components and sub-assemblies of each space-rocket construction and these are a space-rocket fuselage, several spreadable-arms 5, four steering flaps 6, the sectional-load-cover 4, the sliding-engines-cover 7 flat underneath, the sliding-engines-cover 8 wedge-shaped underneath. And on main-space-rocket 2 top can be attached the second-stage-rocket 3 and additional modules.

The views on FIG. 4, 5, 6, 7 show the space-rockets launch method in the utter system for multiple use of several space-rockets equipped with several spreadable-arms 5. Here is shown the harbor terminal for three jointed space-rockets launch preparation, liftoff and later unloading from the ship 10. Whereas FIG. 4 is the side view, FIG. 5 is the top view, FIG. 6 is the front view and FIG. 7 is also the side view. This harbor terminal is at harbor wharf. The harbor terminal comprises two movable ground-gantries 104 and one movable ground-crane 105 for the space-rockets reloading. The movable ground-crane 105 is a lot bigger than both ground-gantries 104. The ground-crane 105 has some beams which reach up somewhat above the ship so that this ground-crane 105 could lift one space-rocket and subsequently shift this space-rocket on both ground-gantries 104. The entire ground-crane 105 will move backwards shortly before the space-rockets launch. Both movable ground-gantries 104 serve for three space-rockets lading after unloading from the ship 10. And later these two ground-gantries 104 serve for three space-rockets launch preparation all time in vertical position thus during hanging on these two ground-gantries 104. And therefor all space-rockets can liftoff from two ground-gantries 104 whilst these space-rockets vertically hang on their spreadable-arms 5. It even include that three joined space-rockets can liftoff this way. Both movable ground-gantries 104 will spread apart on two sides immediately after the space-rockets liftoff. Current FIG. 4-6 show the method of three space-rockets liftoff from the harbor terminal according to current invention. Here three joined space-rockets hang on their all spreadable-arms 5 on two ground-gantries 104 and will liftoff this way. These three joined space-rockets are the same like on further FIG. 268-269 and these are one main-space-rocket 2 which is joined on both sides with two booster-space-rockets 1. On main-space-rocket 2 top it is mounted the assemblage which consist of the second-stage-rocket 3 and the sectional-load-cover 4. Inside this sectional-load-cover 4 is fastened some load which will be carried out on Earth's orbit. These three joined space-rockets all time had entirely lifted upward (spread out) their all spreadable-arms 5 and all time hung on them on two ground-gantries 104 until the liftoff. All time in such vertical position these three space-rockets were overhauled, refit and prepared for launching. And in such status these three joined space-rockets are entirely ready for launch toward space self-evidently from these two movable ground-gantries 104.

On FIG. 4, 5 the arrows show the moving directions of both ground-gantries 104 after three joined space-rockets liftoff. It is so, because both movable ground-gantries will spread apart on two sides immediately after the space-rockets liftoff. And on current FIG. 4 is also sketched the side drawing of one ground-crane 105, because it earlier moved away. This ground-crane 105 is shown in its working place on further FIG. 9, 10. And FIG. 7 is the side view of these three joined space-rockets which are awhile after the liftoff and the side view of two ground-gantries 104 which are spread somewhat apart on two sides. Thereby, the exhaust-fumes 9 gush down of all main engines of these three joined space-rockets. Currently these three joined space-rockets have already a lot lowered down their all spreadable-arms 5. The flow of air pushing down all spreadable-arms 5 which by awhile will be entirely lowered down thus will be alongside their space-rockets fuselages. Current views show that there is possible liftoff of three joined space-rockets which before the liftoff hanged on their all spreadable-arms 5 and which were laid on two ground-gantries 104.

The space-rocket liftoff from two ground-gantries creates also a few benefits like possibility of smooth igniting the main engines, smooth adjusting the space-rocket initial vertical position. Moreover it makes possible to abort the space-rocket liftoff plenty seconds after liftoff. That mean after liftoff and some space-rocket failure to descend the whole space-rocket down and hang it back on two ground-gantries. It would be reverse process in comparison to the liftoff, thus like from FIG. 7 to FIG. 4. Furthermore current views target presentation that construction of such harbor terminal is very simple and is very suitable for unloading the hanging space-rockets from the ship 10 after her arriving to this harbor terminal and such coincidence is shown on further FIG. 9-10. As result of such method space-rockets launches and their quick return to this harbor terminal there is possible their very fast renewed launch, for example several hours after landing on ship 10. Therefor this utter system includes the method of three jointed space-rockets launch preparation all time in vertical position.

FIG. 8 is a prospectus presentation which shows many crowd scenes in the utter system for multiple use of several space-rockets equipped with several spreadable-arms 5. The current whole presentation shows the methods of three joined space-rockets launch and entire ascent process toward the Earth's orbit, descent and vertical landing with the return-load according to current invention. Hence this FIG. 8 shows for example plurality drawing statuses of three joined space-rockets with their liftoff, joined ascent, their separation, further separated ascent toward the Earth's orbit, deploy the load 100, dock the return-load 106, and their individual descending and vertical landing aboard the ship 10 at open sea. On all space-rocket statuses and alongside the arrows show the directions of their traveling trajectories. On space-rocket statuses in right moments the exhaust-fumes 9 gush down off the space-rockets main engines in actual statuses. These three joined space-rockets are the same like on FIG. 4-7 and FIG. 268-269 and these are one main-space-rocket 2 which is joined on both sides with two booster-space-rockets 1. On main-space-rocket 2 top it is mounted the assemblage which consist of the second-stage-rocket 3 and the sectional-load-cover 4. Inside the sectional-load-cover 4 is fastened the load 100 which will be carried out on Earth's orbit. At beginning these three space-rockets statuses are in two front drawings. The first front drawing shows three joined space-rockets in the first status thus their launch from the harbor terminal and show that directly after the liftoff they entirely lowered down their all spreadable-arms 5. The second front drawings show three separated space-rockets in the second statuses thus after their separation on suitable height. Whereat the main-space-rocket 2 still ascends upward because its all main engines continuously run. Whilst two booster-space-rockets 1 already cut-off their main engines and will soonly steer toward the ship 10. Thereafter all space-rockets statuses are in the side drawings and show their travel trajectories toward the ship 10 which is in the side drawing as well. The main-space-rocket 2 with attached second-stage-rocket 3 and with the load 100 inside the sectional-load-cover 4 ascend together upward toward space until the stop moment on Earth's low orbit. Whereas at the same time, both booster-space-rockets 1 steer themselves down towards the ship 10. One booster-space-rocket 1 endeavors to as quick as possible landing so that it could be quick moved sideways onto two hangers 24. Whilst the second booster-space-rocket 1 endeavors to as latest as possible landing so that it would be as plenty time as possible for moving sideways the first already landed booster-space-rockets 1 onto two hangers 24. Probably it will be enough only a few delay minutes so that the second booster-space-rocket 1 landing could take place. The current view shows the descent trajectories of these two booster-space-rockets 1. Here alongside the space-rocket drawing statuses are the numbers in some small circles which explain the space-rockets landing sequences. The first landing booster-space-rocket 1 has the number one in the small circle and in its last status before landing it has also the top drawing. At this juncture, it is already situated exactly above the ship 10. This space-rocket has already lifted up all its six spreadable-arms 5 whereon it will hang up itself on two damping-wagons 30. The second landing booster-space-rocket 1 has the number two in the small circle. As the third will later land the main-space-rocket 2 and therefor it has the number three in the small circle and in its last status before landing it has also the top drawing. After arriving to Earth's low orbit the main-space-rocket 2 folded out on two sides the sectional-load-cover 4 so that the second-stage-rocket 3 with the load 100 could separate and ascend away toward the Earth's high orbit. It means that the main-space-rocket 2 remains on Earth's low orbit with continuously folded out on two sides the sectional-load-cover 4. The current space-rocket status shows as the main-space-rocket 2 circle around the Earth's globe 101 on low orbit. Whereas the second-stage-rocket 3 with the load 100 after arrival to Earth's high orbit releases this load 100 which travel away loose. The current space-rocket status shows as the second-stage-rocket 3 circle around the Earth's globe 101 on high orbit. And later the second-stage-rocket 3 in the right moment steer itself back to Earth's low orbit so that there dock back to main-space-rocket 2. In order to both space-rockets could attach themselves, they will have to circle the Earth's globe 101 and it can take plenty hours. After both space-rockets attached themselves on low orbit then there will be entirely shut up the sectional-load-cover 4 which in this example is empty. And next the main-space-rocket 2 rotates suitably and ignites its main engines for losing speed and steer earthwards. After cut-off all main engines there is rapidly shut down the sliding-engines-cover 7 and then this main-space-rocket 2 enters into the Earth's atmosphere. On space-rockets drawing statuses only the shut down sliding-engines-cover 7 are marked with the numbers. On one suitable status of this main-space-rocket 2, the external arrows show from what direction strongly crowds atmospheric air into sliding-engines-cover 7 and into bottom conic part of the sectional-load-cover 4. Such space-rocket status will occur during the space-rocket initial entering into the Earth's atmosphere. At that time, the suitable flaps 6 will be very little deflected outside so that only steer the space-rocket descent direction. Whilst ten blocking-bars 54 can be entirely slid outside in order to generate some aerodynamic braking and stabilization in this space-rocket uppermost part. Furthermore, the sectional-load-cover 4 bottom conic part generates large aerodynamic braking and stabilization in the space-rocket uppermost part. After considerable speed losing by main-space-rocket 2, it enters into second time period of descent in the atmosphere. Then all ten spreadable-arms 5 are a little lifted upward and all four flaps 6 are a lot deflected out. After a little lift upward of all ten spreadable-arms 5, they generate large aerodynamic braking and stabilization in the space-rocket upper part. At the same time the sliding-engines-cover 7 can be still shut down. After following considerable speed losing by main-space-rocket 2, it lifted entirely up all ten spreadable-arms 5 and maximally deflected out all four flaps 6. In this descent time period, the flow of atmospheric air strongly pushes upward all spreadable-arms 5 and therefor it is necessary to use all brakes installed in these spreadable-arms 5. After entire lift upward of all ten spreadable-arms 5, they generate maximal aerodynamic braking. Steering of the space-rocket descent direction progress by deflection reduction of the suitable flaps 6. All four flaps 6 are in large sizes so that they could steer the space-rocket descent direction even at low speeds. The main-space-rocket 2 in the same status is shown on larger view on further FIG. 266. The main-space-rocket 2 descends all time toward the ship 10. In the right moment is rapidly opened sliding-engines-cover 7. Then in the right moment ignites the main engines to bring total stop of this space-rocket descent and so that it could hang up itself on two large damping-wagons 31 on both deck-gantries 20. Previous entire landing processes of both booster-space-rockets 1 required performing similar stages like for the main-space-rocket 2.

Earlier described descent processes from the Earth's orbit individually by three space-rockets will end with their vertical landing aboard the ship 10. Therefor both deck-gantries 20 are entirely spread apart in two directions before landing of every space-rocket like it is shown on current view and on plenty other views. In such arrangement both deck-gantries 20 are ready and await landing of every space-rocket. Both deck-gantries 20 can precisely and separably move along the entire ship 10 on two main-rails 19. The main-rails 19 are common for both deck-gantries 20 and it causes that both deck-gantries 20 can roll on their whole-length. Therefor each deck-gantry 20 can roll until direction of the opposite deck-gantry 20, if necessary during landing of some space-rocket. It causes, each space-rocket can land almost on entire length of the ship 10. It shows for example on FIG. 26 whereon are the sketches of both deck-gantries 20 which rolled together maximally to left side on main-rails 19. During descent from the Earth's orbit every space-rocket aims to land exactly in the ship 10 center however it is not possible so that each space-rocket would achieve it with one centimeter accuracy. Therefor short time before landing of each space-rocket, both deck-gantries 20 approach to each over and together place themselves under the landing space-rocket just with one centimeter accuracy because they can precisely move along the ship 10. Furthermore the damping-wagons 30 or 31 also place themselves under this landing space-rocket with one centimeter accuracy because these damping-wagons can precisely move transverse the ship 10 on both deck-gantries 20 tops. It causes that each space-rocket can land almost on entire width of the ship 10. Then each vertically landing space-rocket with lifted upward all spreadable-arms 5 will be able to carefully, gently and precisely hang up itself on two damping-wagons 30 or 31. Both movable deck-gantries 20 and all movable damping-wagons 30 or 31 are absolutely essential at juncture of each space-rocket hanging itself. On two damping-wagons 30 vertically lands one booster-space-rocket 1 as hangs itself on its six spreadable-arms 5. On next two damping-wagons 30 vertically lands one booster-space-rocket 1 as well. Whereas on two large damping-wagons 31 vertically lands one main-space-rocket 2. After each space-rocket hanging itself, all damping-wagons can be in fullness squeezed down. Then two squeezed down damping-wagons 30 can roll over from two deck-gantries 20 tops onto two hangers 24 tops. It is possible because constructions of the entire hangers 24 and of the deck-gantries 20 are entirely adapted with constructions and function of all damping-wagons.

Whereas inside the ship 10 two ballasting-wagons 18 will very quickly and precisely ballast this entire ship to perfectly horizontal position during and after landing of each space-rocket and furthermore during moving each one on some hanger 24. All three space-rockets after their individual landing, hanging itself and fastening aboard the ship 10 are shown on next FIG. 9-10 and on further FIG. 20-22.

The entire current prospectus presentation on FIG. 8 targets presentation that is possible individual, vertical landing as many as three space-rockets equipped with spreadable-arms 5 on one ship 10 at sea. Simultaneously it is very important that these space-rockets can land with attached load and that these landings can progress at very short time intervals for example a few minutes intervals. These landing progresses enable this here entire construction of the ship 10 with its elaborated multi-part landing-station for individual landing, quick sideways moving and remotely-controlled fastening of these space-rockets. If necessary, it is possible to redesign construction of presented here landing-station to version for landing five space-rockets and which could also land in a few minutes intervals.

The views on FIG. 9, 10 show space-rockets vertical unloading method in the utter system for multiple use of several space-rockets equipped with several spreadable-arms 5. Here is shown the method of three space-rockets vertical unloading from the ship 10 at harbor terminal according to current invention. This harbor terminal is at harbor wharf and was earlier shown on FIG. 4-7. This harbor terminal consists of two movable ground-gantries 104 and of one movable ground-crane 105. And FIG. 9 is the top view, FIG. 10 is the front view. Therefor these FIG. 9-10 show the views of the ship 10 which just moored at harbor terminal for unloading of three space-rockets which later can be again launch together or individually.

The ship 10 has deck-mounted multi-part landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. Aboard the ship 10 are hanged and still individually fastened three space-rockets. These are the main-space-rocket 2 and two booster-space-rockets 1 in the same status like shown on further FIG. 20-22. The main-space-rocket 2 has on its top mounted the assemblage which consist of the second-stage-rocket 3 and the sectional-load-cover 4. The ground-crane 105 is a lot bigger than both ground-gantries 104. The movable ground-crane 105 has some beams which reach up somewhat above the ship 10 so that this ground-crane 105 could lift one space-rocket and subsequently shift this space-rocket on both ground-gantries 104. In order to lift from the ship 10 the next space-rockets, they must by themselves move sideways until the ship 10 side. Those space-rockets during moving over will be hanging on their damping-wagons 30 or 31 and on current views the arrows show their moving directions. Before such sideways moving of each space-rocket on two damping-wagons 30 or 31 there must be first released all fastenings of each space-rocket. Inside the ship 10 two ballasting-wagons 18 will quickly and precisely ballast this entire ship to perfectly horizontal position after unloading each space-rocket and during moving over each one sideways. On wharf within reach of the ground-crane 105 stand a new load 100 which will be carried out on Earth's orbit, a reserve second-stage-rocket 3 and a reserve sectional-load-cover 4. On current views, the arrows show the moving directions of the entire ground-crane 105 and its top-crossbar with a hook. The ground-crane 105 will move backwards shortly before the space-rockets launch. On earlier FIG. 4 is sketched the side drawing of the ground-crane 105 because it earlier moved away. Current views target presentation that construction of such harbor terminal is very simple and well fitted for taking delivery of the space-rockets from the ship 10 after hers arriving to this harbor terminal. As result of the space-rockets such return to this harbor terminal there is possible their very fast renewed launch just from this harbor terminal. Current FIG. 9-10 together with earlier FIG. 4-7 show also that all space-rockets can be all the time and constantly in the vertical position during their transport, unloading and launch preparation.

FIG. 11, 12, 13 show three views of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for remotely-controlled fastening of three space-rockets equipped with several spreadable-arms 5. Therefor nearby the ship 10 the views show also one booster-space-rocket 1 which has entirely lifted upward (spread out) all spreadable-arms 5. The views show the ship 10 and the landing-station ready for landing the first booster-space-rocket 1. And the ship 10 in shown here status and arrangement was earlier before landing of the first booster-space-rocket 1. And FIG. 11 is the side view, FIG. 12 is the top view, FIG. 13 is the front view. These FIG. 11-13 are also shown as enlarged on FIG. 270-272. Both deck-gantries 20 are entirely spread apart in two directions before landing of every space-rocket like it is shown on current view. In such arrangement these both deck-gantries 20 are ready and await landing of every space-rocket. Therefor readiness for landing of the first booster-space-rocket 1 relies on entire spreading apart of these both deck-gantries 20 on two opposite directions of this ship 10. Furthermore readiness for landing of the first booster-space-rocket 1 relies also on proper setting of four damping-wagons 30 and two large damping-wagons 31 on both deck-gantries 20 tops. For this reason almost at centers of both deck-gantries 20 tops stand two damping-wagons 30 so that it could hang up on them the first landing booster-space-rocket 1. Whereas remaining two damping-wagons 30 and two large damping-wagons 31 stand inactively on one side of both deck-gantries 20 tops. Furthermore readiness for landing of every space-rocket relies also on levelling of the entire ship 10. For this reason, inside the ship 10 hull are installed two ballasting-wagons 18. These two ballasting-wagons 18 are placed in two tunnels 17 which are transverse to ship 10 hull. Whereat in these two tunnels 17, both ballasting-wagons 18 are currently shifted into such side-setting which maintains exactly horizontal position of the ship 10. Whereas the right places for setting all damping-wagons on both deck-gantries 20 tops are selected in such way which enable carrying out individual landing of three space-rockets. During descent from the Earth's orbit every space-rocket aims to land exactly in the ship 10 center however is not possible so that every space-rocket would achieve it with one centimeter accuracy. Therefor shortly before landing of every space-rocket both deck-gantries 20 place themselves under this landing space-rocket just with one centimeter accuracy because they can precisely move along the entire ship 10. Furthermore the damping-wagons 30 or 31 also place themselves under this landing space-rocket with one centimeter accuracy because these damping-wagons can precisely move transverse the ship 10 on both deck-gantries 20 tops. It causes that each space-rocket can land almost on entire width of the ship 10. Thereat every landing space-rocket with lifted upward all spreadable-arms 5 will be able to softly and precisely hang up itself on two damping-wagons 30 or 31.

All current views show entire joined hull construction of the ship 10 which consists of two long side-hulls 11 and two short central-hulls 12. All these mentioned hulls are permanently fastened with four above-water copular-hulls 13. On each long side-hull 11 surface is a main-board 14. The ship 10 has also installed two huge horizontally movable-decks 15 which can move on both main-boards 14. Both movable-decks 15 are installed directly above all joined hulls. Furthermore FIG. 11 and FIG. 12 show also possibility and range of spreading apart in two directions of these both movable-decks 15. Some arrows show the directions of spreading apart of these movable-decks 15. Currently both movable-decks 15 are pushed to each other and touch on themselves in the ship 10 center. Furthermore both movable-decks 15 are sketched with the dashed lines after their entire spreading apart in two directions. After spreading apart in two directions both movable-decks 15, inside the ship 10 hull will arise the jumbo abyss wherein there is only sea-water. The ship 10 with entirely spread apart in two directions both movable-decks 15 is also shown on FIG. 274-275. Currently the deck-gantries 20 are also entirely spread apart in two directions and therefor here are well visible four long-transverse-rails 47 which are situated on both movable-decks 15. Furthermore on hangers 24 there are not hanged any space-rockets and therefor between every pair of hangers 24 there are well visible four short-transverse-rails 48 which are on some pillars 49 on both main-boards 14. Furthermore here are marked some additional following component members and sub-assemblies of this ship 10; both main deck 14, plurality of wheels 16 of both movable-decks 15, two main-rails 19 (for rolling both deck-gantries 20), plurality of wheels 21 of both deck-gantries 20.

FIG. 14, 15, 16 show three views of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for remotely-controlled fastening of three space-rockets equipped with several spreadable-arms 5. Whereas FIG. 14 is the side view, FIG. 15 is the top view, FIG. 16 is the front view. These views show this ship 10 and the landing-station ready for landing the second booster-space-rocket 1 because on her earlier already landed the first booster-space-rocket 1. Therefor here the ship 10 is with one booster-space-rocket 1 which hangs on two hangers 24 and is already fastened at bottom by means of four rotating-wedges 25. This booster-space-rocket 1 earlier landed and moreover it is still fastened also at bottom by means of four rotating-poles 45 which reach from two grasping-wagons 44. Both grasping-wagons 44 are currently under this booster-space-rocket 1.

Landing process of this booster-space-rocket 1 aboard the ship 10 was following. The booster-space-rocket 1 earlier during landing hung up itself by means of its all spreadable-arms 5 on two damping-wagons 30 which were earlier suitably placed on both deck-gantries 20 tops like on FIG. 11-13. After hanging itself of this first booster-space-rocket 1 on two damping-wagons 30, they became entirely squeezed down and which are well visible on FIG. 45-51 and FIG. 61-66. Furthermore after hanging itself of this first booster-space-rocket 1 on two damping-wagons 30 under this space-rocket moved in two grasping-wagons 44 wherein each having two rotating-poles 45. Jointly four rotating-poles 45 were lifted suitably up to block swinging this space-rocket bottom. After hanging itself of every space-rocket on two damping-wagons 30 or 31, the space-rocket can swing. Hence under every space-rocket can move two grasping-wagons 44 in order to block this swinging. Both grasping-wagons 44 can precisely move on both movable-decks 15 transverse the ship 10. Moreover both grasping-wagons 44 can together move in between one pair of hangers 24. Both grasping-wagons 44 roll on four long-transverse-rails 47 on both movable-decks 15. Each grasping-wagon 44 has two rotating-poles 45 which serve for remotely-controlled blocking swinging of the space-rockets bottoms and for strong fastening of the last landed space-rocket bottom. Because both grasping-wagons 44 are low build and are situated on both movable-decks 15 thus they can move under every space-rocket which will hang itself on two damping-wagons on both deck-gantries 20. Both grasping-wagons 44 can move underneath every space-rocket providing they would lower down their all rotating-poles 45. And then four rotating-poles 45 are lifted upward so that they could suitably block swinging of every space-rocket bottom. As result four rotating-poles 45 can quickly block swinging of every space-rocket bottom and it is absolute necessary for the space-rocket quick moving onto two hangers 24. Whilst the non-swinging booster-space-rocket 1 hangs on two damping-wagons 30 and is blocked at bottom by four rotating-poles 45 so just then it is possible to move this space-rocket to ship side and between one pair of hangers 24, thus to hang this space-rocket onto one pair of hangers 24. In order to perform it, both damping-wagons 30 and both grasping-wagons 44 must move at equal speeds toward one pair of hangers 24. Then both grasping-wagons 44 will roll by from four long-transverse-rails 47 onto four short-transverse-rails 48 which are between one pair of hangers 24. Whereat both damping-wagons 30 with hanged on them one booster-space-rocket 1 will roll by from the upper-long-rails 23 on both deck-gantries 20 onto upper-short-rails 26 on two hangers 24. Currently both damping-wagons 30 stand on upper-short-rails 26 being situated on both hangers 24 tops. Both these damping-wagons 30 stand precisely in centers of two hangers 24 tops. It enabled remotely-controlled fastening at bottom this hanging booster-space-rocket 1 by means of four rotating-wedges 25. Therefor after arriving all wagons between one pair of hangers, the hanged space-rocket will be fastened at bottom by means of four rotating-wedges 25 off two hangers. After fastening at bottom this booster-space-rocket 1 by means of four rotating-wedges 25 it will be possible to loose pressure of four rotating-poles 45. Currently both grasping-wagons 44 are still under the booster-space-rocket 1. Then two external rotating-poles 45 will be possible to lower down like it show the current views with the sketches of lowered down two rotating-poles 45. And next both grasping-wagons 44 will be able to move under the hanged booster-space-rocket 1 toward the ship 1 center. Here show it the sketches of the grasping-wagons 44 in two statuses and arrangements. At that time both grasping-wagons 44 will roll by from four short-transverse-rails 48 onto four long-transverse-rails 47. Among those rails are long intervals however the grasping-wagons 44 are a lot more longer and have plurality of some wheels 43 and therefor these grasping-wagons 44 will easily roll by from the short-transverse-rails 48 onto long-transverse-rails 47 on both movable-decks 15. It is well visible on further FIG. 81, 82 and there these long intervals are indicated with the large exclamation marks. After moving of an entire assemblage with all wagons (with hanged space-rocket) between two hangers 24, this ship 10 and the landing-station are immediately ready for landing the next space-rocket. It is only enough to entirely spread apart both deck-gantries 20 onto ship 10 two directions. Described here course of action for landing of the first space-rocket enables very quick readiness for landing of the next space-rocket. During moving of the booster-space-rocket 1 on two hangers 24, inside the ship 10 in two tunnels 17 both ballasting-wagons 18 were moving at suitable speed to reverse direction so that continually maintain exactly horizontal position of the entire ship 10. As result both ballasting-wagons 18 moved almost entirely aside of the ship 10. In current status on both deck-gantries 20 tops stand remaining two damping-wagons 30 and two large damping-wagons 31. After moving of the first booster-space-rocket 1 on two hangers 24 all remaining damping-wagons rolled by on upper-long-rails 23 on both deck-gantries 20 to suitable arrangement for landing of the second booster-space-rocket 1. Thereby in current status the views show the ship 10 and the landing-station ready for landing the second booster-space-rocket 1. Readiness for landing of the second booster-space-rocket 1 relies like previously on entire spreading apart of both deck-gantries 20 on two opposite directions of this ship 10. Moreover readiness for landing of the second booster-space-rocket 1 relies also on proper setting of two damping-wagons 30 on both deck-gantries 20 tops like are on current views. These two damping-wagons 30 stand almost in centers of two deck-gantries 20 tops so that it could hang up on them the second landing booster-space-rocket 1. Whereas two large damping-wagons 31 stand inactively on one side of both deck-gantries 20 tops. Furthermore readiness for landing of every space-rocket relies also on levelling of the entire ship 10. For this reason, inside the ship 10 hull are installed two ballasting-wagons 18. These two ballasting-wagons 18 are placed in two tunnels 17 which are transverse to ship 10 hull. Whereat in two tunnels 17, both ballasting-wagons 18 are currently shifted almost entirely on ship 10 one side because on opposite side is hanged the booster-space-rocket 1. It causes that the entire ship 10 has equal level.

FIG. 17, 18, 19 show three views of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for remotely-controlled fastening of three space-rockets equipped with several spreadable-arms 5. And FIG. 17 is the side view, FIG. 18 is the top view, FIG. 19 is the front view. These views show this ship 10 and the landing-station ready for landing the third space-rocket because earlier already landed two booster-space-rockets 1. Lately landed the second booster-space-rocket 1 which hung up itself by means of its all spreadable-arms 5 on two damping-wagons 30 which were earlier suitably placed on both deck-gantries 20 tops like on previous FIG. 14-16. Entire landing process, hanging itself and moving of the second booster-space-rocket 1 on two hangers 24 was the same like during entire process of the first booster-space-rocket 1 and which was described in FIG. 14-16. Current views show the ship 10 with two booster-space-rockets 1 whereas each one hangs on two hangers 24 and each one is fastened at bottom by means of four rotating-wedges 25. These two space-rockets earlier landed and currently the views show this ship 10 and the landing-station ready for landing the third space-rocket which will be the main-space-rocket 2. Readiness for landing of the main-space-rocket 2 relies like previously on entire spreading apart of both deck-gantries 20 on two opposite directions of this ship 10. Furthermore this readiness also relies on setting two large damping-wagons 31 at centers of two deck-gantries 20 tops like on current views. These two large damping-wagons 31 stand now in centers of two deck-gantries 20 tops so that it could hang up on them the main-space-rocket 2. Furthermore readiness for landing of every space-rocket relies also on levelling of the entire ship 10. For this reason, inside the ship 10 hull are installed two ballasting-wagons 18. These two ballasting-wagons 18 are placed in two tunnels 17 which are transverse to ship 10 hull. Whereat in two tunnels 17, both ballasting-wagons 18 are currently shifted to ship 10 center and it currently maintains exactly horizontal position of this ship 10.

FIG. 20, 21, 22 show three views of the entire ship 10 which has deck-mounted multi-part landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. Whereas FIG. 20 is the side view, FIG. 21 is the top view, FIG. 22 is the front view. These views show the ship 10 with three individually hanged and fastened space-rockets and which are ready for transporting over sea for unloading at harbor terminal. On this ship 10 earlier landed two booster-space-rockets 1 and furthermore as the third landed the main-space-rocket 2. Here this main-space-rocket 2 hangs at centers of two deck-gantries 20 and is fastened at bottom by means of four rotating-poles 45 which reach from two grasping-wagons 44. As the last, landed just this main-space-rocket 2 which hung up itself by means of its all ten spreadable-arms 5 on two large damping-wagons 31 which were earlier placed at centers of two deck-gantries 20 tops like on previous FIG. 17-19. After the main-space-rocket 2 hanging itself, both large damping-wagons 31 became entirely squeezed down which is visible on FIG. 20, 22. During the same time, both grasping-wagons 44 stood inactively on ship 10 one side and had lifted up all four rotating-poles 45. And after the main-space-rocket 2 completely hanged up itself, both grasping-wagons 44 completely lowered down two rotating-poles 45 on one side to horizontally setting. It enabled unrestricted moving of both grasping-wagons 44 underneath this hanged main-space-rocket 2. Therefor then these two grasping-wagons 44 moved under this main-space-rocket 2. And then two rotating-poles 45 which were continuously upward touched on with the main-space-rocket 2. And then both grasping-wagons 44 lifted upward two horizontally set rotating-poles 45 which touched on with the main-space-rocket 2 as well. And then all four rotating-poles 45 together suitably and gradually blocked swinging of this space-rocket bottom. Next all four rotating-poles 45 strongly tightened themselves to this main-space-rocket 2 and it strongly fastened this main-space-rocket 2 bottom part. On FIG. 22 are shown the grasping-wagons 44 rolling under this space-rocket by means of the sketches in two statuses. Further views on FIG. 83-85 show the enlarged views of the grasping-wagons 44 which by means of four rotating-poles 45 strongly fastened one main-space-rocket 2 bottom. This main-space-rocket 2 landed with attached second-stage-rocket 3 and the sectional-load-cover 4 which could have inside some return-load from the Earth's orbit. Whereat in two tunnels 17, both ballasting-wagons 18 are now shifted to ship 10 center and it maintains exactly horizontal position of this ship 10. Like it was earlier mentioned the current views show the ship 10 in fullness loaded with three space-rockets and ready for seafaring for unloading at harbor terminal. Presented here the ship 10 with landing-station having strong fastening of the space-rockets enables sea-transportation even at stormy sea. Whereat in two tunnels 17, both ballasting-wagons 18 serve also for automatic, continuous, quick and precise ballasting of this ship 10 during seafaring. Furthermore the current views somewhat show that the upper-short-rails 26 on hangers 24 fit to upper-long-rails 23 on both deck-gantries 20 whilst these both deck-gantries 20 stand at ship 10 center. Consequently, the damping-wagons 30 with the hanged space-rockets could earlier roll by on hangers 24. Such fitting of these rails will be later also necessary for vertical unloading all space-rockets from this ship 10. It is shown on previous FIG. 9-10.

FIG. 23, 24, 25 show three views of the alone entire multi-part landing-station for individual, vertical landing of three space-rockets. FIG. 23 is the side view, FIG. 24 is the top view, FIG. 25 is the front view. This multi-part landing-station is in the same arrangement like aboard the ship 10 however the current views are without the grasping-wagons 44. This multi-part landing-station for vertical landing of three space-rockets consist of two pairs of hangers 24 and of two deck-gantries 20. Two space-rockets after landing can be quick moved from two deck-gantries 20 to four hangers 24. Hence in the landing-station are mounted four hangers 24 this way that one par of hangers 24 is mounted on each side of the ship 10. The hangers 24 in construction reminds immovable towers. Each hanger 24 has two rotating-wedges 25 which serve for remotely-controlled fastenings of one space-rocket. One par of hangers 24 serve for hanging one space-rocket and fastening it by means of four rotating-wedges 25. On each hanger 24 top are two upper-short-rails 26. Whereas on each deck-gantry 20 top are two upper-long-rails 23. Therefor on both deck-gantries 20 tops are together four upper-long-rails 23 whereon stand four damping-wagons 30 and two large damping-wagons 31. Both deck-gantries 20 can separably roll along the entire ship 10 on two main-rails 19. For rolling both deck-gantries 20 use their own plurality wheels 21. Furthermore in both deck-gantries 20, each one has two bumpers 22 distinctly protruding forwards. Currently both deck-gantries 20 are entirely spread apart in two directions, the same like on earlier FIG. 11-19 and next FIG. 270-272. Presented on current views the landing-station for individual, vertical landing of three space-rockets can also be built entirely on shore. And then it will not be necessary to install all space-rocket fastenings which are applied aboard the ship 10.

FIG. 26, 27, 28 show three views of two whole deck-gantries 20 by themselves which are in the same arrangement like aboard the ship 10 and the same like on FIGS. 1-3 and 11-13. And FIG. 26 is the side view, FIG. 27 is the top view, FIG. 28 is the front view. Currently both deck-gantries 20 approached to each other because earlier rolled on their own plurality wheels 21 on two main-rails 19. After approaching to each other, both deck-gantries 20 touch on themselves with the bumpers 22. Both deck-gantries 20 can precisely and separably roll on main-rails 19 along the entire ship 10. These main-rails 19 are common for both deck-gantries 20 and it causes that both deck-gantries 20 can roll on their whole-length. Therefor each deck-gantry 20 can roll until direction of the opposite deck-gantry 20, if necessary during landing of some space-rocket. It causes that each space-rocket can land almost on entire length of the ship 10. While on all drawings there are shown only landings examples in the ship center. On FIG. 26 shows it the sketch of both deck-gantries 20 which rolled together maximally to left side on main-rails 19. On both deck-gantries 20 tops are together four upper-long-rails 23 whereon stand four damping-wagons 30 and two large damping-wagons 31.

FIG. 29, 30, 31 show three views of two pairs of hangers 24 in the same arrangement like aboard the ship 10. Whereas FIG. 29 is the side view, FIG. 30 is the top view, FIG. 31 is the front view. All hangers 24 are permanently fastened onto main deck 14 of the ship 10 and therefor are immobile. The hangers 24 in construction reminds immovable towers. On each hanger 24 top there are two upper-short-rails 26. Moreover each hanger 24 has two rotating-wedges 25 which serve for remotely-controlled fastening of the space-rockets. The opposite hangers 24 have the rotating-wedges 25 mounted on varied heights so that they would not hook each over. Consequently every space-rocket can be fastened by four rotating-wedges 25 which are on one pair of hangers 24. Furthermore here are also visible some rotary-actuators 27 which rotate the rotating-wedges 25.

FIG. 32, 33, 34 show three enlarged views of one pair of hangers 24 wherein each has two rotating-wedges 25 lowered down and with the arrows showing their rotating directions. Each rotating-wedge 25 has its own rotary-actuator 27. And FIG. 32 is the side view, FIG. 33 is the top view, FIG. 34 is the front view. The hangers 24 are permanently fastened onto main deck 14 of the ship 10 and thus are immobile. On each hanger 24 top there are two upper-short-rails 26 whereon can roll in one damping-wagon 30.

FIG. 35, 36, 37 show the enlarged views of one pair of hangers 24 with the space-rocket-tube 51 fragment which is fastened by means of four rotating-wedges 25. These four rotating-wedges 25 are rotated in such way that they all together tighten up this space-rocket-tube 51 fragment. Whereas FIG. 35 is the side view, FIG. 36 is the top view, FIG. 37 is the front view.

FIG. 38 is the top view of the horizontal sectional view according to S-S line on FIG. 35. Here, from above are visible four rotating-wedges 25 tightening the space-rocket-tube 51 fragment. The enlarged views of the rotating-wedges 25 are shown on FIG. 45-54.

FIG. 39, 40, 41 show three enlarged views of one pair of hangers 24 whereon tops in the upper-short-rails 26 stand two damping-wagons 30. FIG. 39 is the side view, FIG. 40 is the top view, FIG. 41 is the front view. The two damping-wagons 30 are not squeezed down because they are not loaded with any space-rocket.

FIG. 42, 43, 44 show three enlarged views of one pair of hangers 24 with hanged and fastened one booster-space-rocket 1. And FIG. 42 is the side view, FIG. 43 is the top view, FIG. 44 is the front view. This booster-space-rocket 1 all six spreadable-arms 5 lay on two damping-wagons 30 which are entirely squeezed down by weight of this space-rocket. Simultaneously the booster-space-rocket 1 in its bottom is fastened by means of four rotating-wedges 25. The current views are very similar to previous FIG. 32-38 however here are additionally two damping-wagons 30 and the entire booster-space-rocket 1. Aboard the ship 10 fastening of every space-rocket bottom is absolutely necessary for seagoing even at small sea-waving. Without fastening of the space-rocket bottoms, these space-rockets would swing during a little rolling the ship 10. Presented here the fastening solutions of the space-rockets bottoms are very strong and these enable the sea-transportation of these space-rockets even at hefty sea-waving.

FIG. 45, 46, 47 show three enlarged views of the rotating-wedges 25 with some hanger 24 fragments sketches which are performed with the dashed lines. All four rotating-wedges 25 are completely lowered down and with the arrows showing their rotating directions. And FIG. 45 is the side view, FIG. 46 is the top view, FIG. 47 is the front view. The opposite hangers 24 have the rotating-wedges 25 mounted on varied heights so that they would not hook each over.

FIG. 48, 49, 50 show three enlarged views of four rotating-wedges 25 which are rotated in such way that they all together tighten up the space-rocket-tube 51 fragment. FIG. 48 is the side view, FIG. 49 is the top view, FIG. 50 is the front view. Each rotating-wedge 25 has flexible coatings in suitable places, marked with some dots on views. These flexible coatings are intended for direct contacts with the space-rockets.

FIG. 51 is the top view and shows for example the space-rocket bottom that is moved away from correct location. If some space-rocket accidentally hung up itself aslant then all rotating-wedges 25 will enable pushing this space-rocket to as best location as its possible in order to fasten this space-rocket. It shows this FIG. 51 and here two upper rotating-wedges 25 are pushing this space-rocket bottom.

FIG. 52, 53, 54 show three a lot enlarged views of two rotating-wedges 25 which are completely lowered down. Whereas FIG. 52 is the side view, FIG. 53 is the top view, FIG. 54 is the front view. Two rotating-wedges 25 which are installed on one hanger 24, have a common support-axle 28. Each rotating-wedge 25 has its own rotating-axle 29 with its own rotary-actuator 27. Thus each rotating-wedge 25 can rotate apart other rotating-wedges 25.

FIG. 55, 56, 57 show three a lot enlarged views of one pair of hangers 24 upper part in the same statuses like were earlier shown on FIG. 39-41. Whereas FIG. 55 is the side view, FIG. 56 is the top view, FIG. 57 is the front view. On hangers 24 tops and on upper-short-rails 26 stand two damping-wagons 30. These two damping-wagons 30 are not squeezed down because they are not loaded with any load. On both damping-wagons 30 tops are situated thick flexible-layers 32 which are marked with the dots on views. Furthermore there are also permanently fastened flexible wedge-shaped-fenders 33 in the uppermost and bottom part of each damping-wagon 30. There are also visible all leading-shafts 34 in not squeezed down both damping-wagons 30.

FIG. 58, 59, 60 show three a lot enlarged views of one pair of hangers 24 upper part in the same statuses like were earlier shown on FIG. 42-44. Whereas FIG. 58 is the side view, FIG. 59 is the top view, FIG. 60 is the front view. Here on one pair of hangers 24 is hanged one booster-space-rocket 1. All six spreadable-arms 5 of this one booster-space-rocket 1 lay on two damping-wagons 30 which are in fullness squeezed down by weight of this space-rocket. All six spreadable-arms 5 penetrated and couched on two thick flexible-layers 32 on both damping-wagons 30 tops. Furthermore there are also visible four flexible wedge-shaped-fenders 33 whereon is leaned against the booster-space-rocket 1 fuselage. It is also visible that squeezed down both damping-wagons 30 lowered down their all leading-shafts 34 and which do not hook and collide with any components of the hangers 24 and of the deck-gantries 20. On FIG. 59 from above are visible four rotating-wedges 25 which fastened the booster-space-rocket 1 bottom. Consequently, constructions of the entire hangers 24 and of the deck-gantries 20 are entirely adapted with constructions and function of all damping-wagons 30 and large damping-wagons 31. Therewith the squeezed down damping-wagons 30 are able to move over from two deck-gantries 20 onto two hangers 24. All current views also show that the damping-wagons 30 and the large damping-wagons 31 have damping high range during hanging on them the space-rockets equipped with several spreadable-arms 5. This damping high range of all damping-wagons influence very beneficially on durability of all fastenings which upbear the spreadable-arms 5 onto space-rocket fuselage.

FIG. 61, 62, 63 show three a lot enlarged views of two damping-wagons 30 which are not squeezed down and they stand on upper-short-rails 26 which are on tops of one pair of hangers 24. FIG. 61 is the side view, FIG. 62 is the top view, FIG. 63 is the front view. These two damping-wagons 30 are in the same setting like on previous FIG. 55-57. Here is visible construction of two damping-wagons 30 and their interrelationship because for one space-rocket hanging itself there are necessary two damping-wagons 30.

FIG. 64, 65, 66 show three a lot enlarged views of two damping-wagons 30 and which for example are squeezed down and stand on upper-short-rails 26 which are on tops of one pair of hangers 24. FIG. 64 is the side view, FIG. 65 is the top view, FIG. 66 is the front view. These two damping-wagons 30 are in the same setting like on previous FIG. 58-60. Here is visible that squeezed down both damping-wagons 30 lowered down their all leading-shafts 34. Here, except of the upper-short-rails 26 there are not other fragments of the hangers 24. The damping-wagons 30 are described in fullness on next FIG. 67-71.

FIG. 67, 68, 69, 70, 71 show several a lot enlarged views and the horizontal sectional view and a bottom projection of one entire damping-wagon 30 which is not squeezed down and in different manner than previously, stands on two upper-long-rails 23 which are on one deck-gantry 20 top. Whereas FIG. 67 is the side view, FIG. 68 is the top view in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. And FIG. 69 is the front view, FIG. 70 is the bottom projection. And FIG. 71 is the top view of the horizontal sectional view according to S-S line on FIG. 69. There are visible all sub-assemblies and construction of one damping-wagon 30. Each damping-wagon 30 has one main-plate 35 with on both sides permanently fastened six high-leading-tubes 36. Under the main-plate 35 are installed four driving-wheels 41, four leading-wheels 42 and a battery 43. In all driving-wheels 41 are installed electric motors powered of the battery 43. Above the main-plate 35 are permanently fastened the bottoms of six conic-springs 39 in vertical setting. Whereat these six conic-springs 39 tops are permanently fastened to being situated above them a middle-plate 38. This middle-plate 38 has on both sides permanently fastened six low-leading-tubes 37 which are the very same spaced out like the high-leading-tubes 36 in the main-plate 35. Above the middle-plate 38 are permanently fastened the bottoms of six conic-springs 39 in vertical setting and the very same way like on main-plate 35. Whereat those six conic-springs 39 tops are permanently fastened to being situated above them the next middle-plate 38. This next middle-plate 38 is the same like the previous middle-plate 38. Presented here, one damping-wagon 30 has three middle-plates 38 with some conic-springs 39 in the very same settings and fastenings. Whereat tops of six uppermost conic-springs 39 are permanently fastened to being situated above them a top-plate 40. This top-plate 40 has on both sides permanently fastened six leading-shafts 34 which are spaced out suitably to being situated under them the low-leading-tubes 37 in all middle-plates 38 and all high-leading-tubes 36 in the main-plate 35. Presented here the construction solution of one damping-wagon 30 has the leading-shafts 34 in two diameters. It is not needed and they can be equal. Above the top-plate 40 is permanently fastened the thick flexible-layer 32 which is marked with the dots on views. On this flexible-layer 32 will couch all six spreadable-arms 5 which are applied in the booster-space-rocket 1. Moreover to top-plate 40 and to flexible-layer 32 on one side is permanently fastened the flexible wedge-shaped-fender 33. The same flexible wedge-shaped-fender 33 is also permanently fastened to main-plate 35 one side. As result of such solution, one damping-wagon 30 has four layers of the conic-springs 39 which can be in fullness squeeze down and which create damping high range. The damping-wagons 30 are designed for rolling by from the upper-long-rails 23 on both deck-gantries 20 onto upper-short-rails 26 on hangers 24. It is possible because the upper-short-rails 26 on hangers 24 fit to upper-long-rails 23 on both deck-gantries 20 whilst these both deck-gantries 20 stand at ship 10 center. It means the damping-wagons 30 can be situated on deck-gantries 20 or on hangers 24. All upper-long-rails 23 and all upper-short-rails 26 are in C-profiles and thus all damping-wagons cannot fall out off them.

FIG. 72, 73, 74 show three a lot enlarged views of one entire damping-wagon 30 and which for example is squeezed down and does not stand on any rails. And FIG. 72 is the side view. And FIG. 73 is the top view of one damping-wagon 30 in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. And FIG. 74 is the front view. Here is visible that all conic-springs 39 are entirely squeezed down. Whereat all conic-springs 39 in the highest layer are perfectly entirely squeezed down. Whereat all conic-springs 39 in the lower three layers are squeezed down to low-leading-tubes 37 height. Here is also visible that all leading-shafts 34 over-passed all low-leading-tubes 37 and all high-leading-tubes 36. As result all leading-shafts 34 are hanging by themselves down under the damping-wagon 30. This solution of the leading-shafts 34 which are fitted with all leading tubes creates damping high range and simultaneously maintains unshaken and stable top surface of all damping-wagons during squeezing down by space-rocket.

FIG. 75, 76, 77, 78, 79 shows several a lot enlarged views and the horizontal sectional view and the bottom projection of one large damping-wagon 31 which is not squeezed down and stands on two upper-long-rails 23 which are on one deck-gantry 20 top. Whereas FIG. 75 is the side view. And FIG. 76 is the top view of one large damping-wagon 31 in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. And FIG. 77 is the front view, FIG. 78 is the bottom projection. And FIG. 79 is the top view of the horizontal sectional view according to S-S line on FIG. 77. This large damping-wagon 31 has the same construction like the damping-wagon 30 however is longer. For this reason each large damping-wagon 31 has six driving-wheels 41 and ten conic-springs 39 in each layer. The large damping-wagons 31 are longer so that could lay on them all ten spreadable-arms 5 which are applied in the main-space-rocket 2. Increased number of the conic-springs 39 create also damping larger capacity which is necessary during hanging itself of the main-space-rocket 2 with attached additional modules or assemblages. The large damping-wagons 31 are not designed for rolling by on upper-short-rails 26 on hangers 24. Instead both large damping-wagons 31 are designed only for remaining and rolling on upper-long-rails 23 on both deck-gantries 20.

FIG. 80, 81, 82 show three views of two grasping-wagons 44 wherein each with two rotating-poles 45. These two grasping-wagons 44 stand on four short-transverse-rails 48. The current views show the rotating-poles 45 lifted upward to setting similar like during holding the space-rocket. Whereat the sketches of two right rotating-poles 45 together with the arrows show their total possible rotation range. Whereas FIG. 80 is the side view, FIG. 81 is the top view, FIG. 82 is the front view. The short-transverse-rails 48 are based on several pillars 49 which are situated between two hangers 24 and visible on a lot views. All pillars 49 stand on two main-boards 14 which are on two long side-hulls 11. Both grasping-wagons 44 have plurality of the wheels 46 in order to they could roll by long intervals which are between the short-transverse-rails 48 and the long-transverse-rails 47. These intervals are best visible on FIG. 81-82 and are indicated with the large exclamation marks. Both grasping-wagons 44 wherein each has two rotating-poles 45 with spherical ends which have flexible coatings. These flexible coatings are intended for direct contacts with the space-rockets.

FIG. 83, 84, 85 show three views of two grasping-wagons 44 which stand on four long-transverse-rails 47. These both grasping-wagons 44 by means of four rotating-poles 45 tighten one main-space-rocket 2 bottom in the same way like on earlier FIG. 20-22 though on those FIGs. many of the components are veiled by other members. Whereas FIG. 83 is the side view, FIG. 84 is the top view, FIG. 85 is the front view. Furthermore on current views, the sketches of all inclined down rotating-poles 45 together with the arrows show their required inclination down, so that the entire grasping-wagons 44 could move underneath this hanged main-space-rocket 2. It is best visible on FIG. 85 and somewhat on FIG. 83 and it is indicated with two large exclamatory signs. Furthermore on FIG. 81-82, 84-85 the arrows on grasping-wagons 44 show their possible moving directions.

FIG. 86A, B and FIG. 87 and FIG. 88A, B show three views of one booster-space-rocket 1 upper and bottom parts which has six spreadable-arms 5, four steering flaps 6 and one sliding-engines-cover 7. Whereas FIG. 86A is the side view of one booster-space-rocket 1 upper part. And FIG. 86B is the side view of one booster-space-rocket 1 bottom part. And FIG. 87 is the top view in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. And FIG. 88A, B are the front views. On current views the sliding-engines-cover 7 is entirely lifted upward and it uncovered all nozzles 85 of this space-rocket main engines. Here all spreadable-arms 5 are entirely lowered down and consequently are alongside the space-rocket fuselage. Whereat all four flaps 6 are vertically set and are entirely inside the space-rocket fuselage. On FIG. 86A, B and FIG. 88A,B the external arrows show the spreading directions of the spreadable-arms 5 and deflection of the flaps 6.

More information about the spreadable-arms 5 mounted on each space-rocket.

The quantity of the spreadable-arms 5 mounted on each space-rocket depends on its weight. Therefor currently in one booster-space-rocket 1 are mounted six spreadable-arms 5. These spreadable-arms 5 are suitably spaced out in each space-rocket fuselage so that they all could completely spread out on two sides. Here presented utter system for multiple use of the space-rockets is completely connected with utilization of several spreadable-arms 5 mounted on all space-rockets. Therefor these spreadable-arms 5 are absolutely necessary, are utilized multiple times and are the main characteristic feature of this utter system. These spreadable-arms 5 create many possibilities. First of all and the most important is that each space-rocket lands on its spreadable-arms 5 as hangs itself on them.

And later spreadable-arms 5 are used as the aerodynamic brake and the space-rockets land as hang themselves on these spreadable-arms 5. Because all spreadable-arms 5 are designed and build as very strong therefor during space-rocket descent they can be lifted upwards (spread out) on very high altitude for use as the aerodynamic brake. As result of long-lasting aerodynamic braking caused by spreadable-arms 5, it will be necessary to use far less space-rocket fuel at landing engine burn so that each space-rocket could hang up itself. Each spreadable-arm 5 is moved by one moving mechanism installed inside the space-rocket fuselage. Therefor every spreadable-arm 5 is moved independently from other spreadable-arms 5. And it causes that if some spreadable-arm 5 fail to lift upward thus then the others will lift upward anyway and the whole space-rocket will be able to land on them. In some circumstances, the spreadable-arms 5 can also be used for emergency steering direction of the space-rocket descent. It is so because the spreadable-arms 5 can be differently and fluently lowered down and lifted upward for emergency steering the space-rocket descent. In this utter system, the spreadable-arms 5 are mounted on space-rockets upper parts and it causes that the space-rockets bottom parts are without some legs for landing. As result, in the space-rockets bottom parts is plenty room for installing the sliding-engines-covers 7 or 8 which are presented in current invention and which are so much needed. More information about construction of each spreadable-arm 5 begins in description of further FIG. 119-121.

FIG. 89A, B and FIG. 90 show two views of one booster-space-rocket 1 upper and bottom parts which has a little lifted upward all six spreadable-arms 5 and consequently they a little protrude outside the space-rocket fuselage. Whereat all four flaps 6 are a lot deflected out and consequently protrude outside the space-rocket fuselage. Whereat the sliding-engines-cover 7 is entirely lifted upward. Whereas FIG. 89A is the side view of one booster-space-rocket 1 upper part. And FIG. 89B is the side view of one booster-space-rocket 1 bottom part. And FIG. 90 is the top view of FIG. 89A, B in the same arrangement and situation. On FIG. 89A, B the arrows show the spreading directions of the spreadable-arms 5 and deflection of the flaps 6. On FIG. 89A, B, on space-rocket fuselage are clearly visible several corner-beams 52 which lead sliders 53 of the spreadable-arms 5.

FIG. 91A, B and FIG. 92 and FIG. 93A, B show three views of one booster-space-rocket 1 upper and bottom parts. This booster-space-rocket 1 has entirely lifted upward all six spreadable-arms 5 and consequently they are completely spread out on two sides. And therefor these spreadable-arms 5 are transverse the space-rocket fuselage. Furthermore currently all blocking-bars 54 are entirely slid outside the space-rocket fuselage and it entirely blocked all middle-beams 55 in all spreadable-arms 5. Whereat all four flaps 6 are entirely deflected out and consequently are horizontally and transverse the space-rocket fuselage. Whereat the sliding-engines-cover 7 is entirely lifted upward and it uncovered all nozzles of the main engines. Whereas FIG. 91A is the side view of one booster-space-rocket 1 upper part. And FIG. 91B is the side view of one booster-space-rocket 1 bottom part. And FIG. 92 is the top view in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. And FIG. 93A is the front view of one booster-space-rocket 1 upper part. And FIG. 93B is the front view of one booster-space-rocket 1 bottom part. On FIG. 91A and FIG. 93A, on space-rocket fuselage are also clearly visible several corner-beams 52 which lead the sliders 53 of the spreadable-arms 5.

FIG. 94A, B and FIG. 95 and FIG. 96A, B show three views of one main-space-rocket 2 upper and bottom parts which has ten spreadable-arms 5, four steering flaps 6 and one sliding-engines-cover 7. Currently all spreadable-arms 5 are entirely lowered down and consequently are alongside the space-rocket fuselage. The quantity of spreadable-arms 5 mounted on each space-rocket depends on its weight. Therefor currently in one main-space-rocket 2 are mounted ten spreadable-arms 5. These spreadable-arms 5 are suitably spaced out in each space-rocket fuselage so that they all could completely spread out on two sides. Whereat all four flaps 6 are vertically set and entirely inside the space-rocket fuselage. Whereat the sliding-engines-cover 7 is entirely lifted up and it uncovered all nozzles of the main engines. And FIG. 94A, B are the side views, FIG. 95 is the top view in two equal views which are rotated 90 degrees in relation to each other so that they cohere to below views. And FIG. 96A, B are the front views. On FIG. 94A, B and FIG. 96A, B the arrows show the spreading directions of the spreadable-arms 5 and deflection of the flaps 6. On FIG. 95 are visible the linear-actuators 60 which steer deflections of the flaps 6. On FIG. 94A, B and FIG. 96A, B, these linear-actuators 60 are sketched with the dashed lines because they are situated inside the space-rocket fuselage.

FIG. 97A, B and FIG. 98 and FIG. 99A, B show three views of one main-space-rocket 2 upper and bottom parts which has entirely lifted upward all ten spreadable-arms 5 and consequently they are completely spread out on two sides. And therefor these spreadable-arms 5 are transverse the space-rocket fuselage. Moreover now all blocking-bars 54 are entirely slid outside the space-rocket fuselage and it entirely blocked all middle-beams 55 in all spreadable-arms 5. Whereat all four flaps 6 are entirely deflected out and consequently are horizontally and transverse the space-rocket fuselage. On all views are visible the linear-actuators 60 which steer deflections of the flaps 6. Whereat the sliding-engines-cover 7 is entirely lifted upward. And FIG. 97A, B is the side view. And FIG. 98 is the top view in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. And FIG. 99A, B is the front view. On FIG. 97A, B are clearly visible several whole corner-beams 52 on this space-rocket fuselage. These corner-beams 52 lead the sliders 53 of the spreadable-arms 5.

FIG. 100, 101 show two views of one booster-space-rocket 1 upper part and of two deck-gantries 20 upper part whereon tops stand two damping-wagons 30 and which are not squeezed down. These views show just vertically landing the booster-space-rocket 1 which in a moment will hang itself on two damping-wagons 30. This space-rocket has entirely lifted upward (spread out) all six spreadable-arms 5 which do not lay yet on flexible-layers 32 on damping-wagons 30. Whereat four flaps 6 are entirely deflected outside the space-rocket fuselage. And FIG. 100 is the side view, FIG. 101 is the top view. On FIG. 101 are visible four flexible wedge-shaped-fenders 33 whereon the space-rocket fuselage is already leaned against in despite of, this space-rocket does not yet hang up itself on both damping-wagons 30. On FIG. 101 is not shown below situated the sliding-engines-cover 7. Current views show fitting way of both damping-wagons 30 with six spreadable-arms 5 in one booster-space-rocket 1. Current views are a little similar to FIG. 42-43 and FIG. 58-59 and there one booster-space-rocket 1 already hangs on squeezed down two damping-wagons 30 but which stand on two hangers 24.

FIG. 102, 103 show two views of one main-space-rocket 2 upper part and of two deck-gantries 20 upper part whereon tops stand two large damping-wagons 31 and which are not squeezed down. These views show just vertically landing main-space-rocket 2 which in a moment will hang up itself on two large damping-wagons 31. This space-rocket has entirely lifted upward (spread out) all ten spreadable-arms 5 which do not lay yet on flexible-layers 32 on these large damping-wagons 31. Whereat four flaps 6 are entirely deflected outside the space-rocket fuselage. Whereas FIG. 102 is the side view, FIG. 103 is the top view. On FIG. 103 are visible four flexible wedge-shaped-fenders 33 whereon is already leaned against this space-rocket fuselage in despite of this space-rocket does not hang up yet on both large damping-wagons 31. On FIG. 103 is not shown below situated the sliding-engines-cover 7. The current views target showing fitting way of both large damping-wagons 31 with ten spreadable-arms 5 in one main-space-rocket 2.

FIG. 104, 105, 106 show three views of four steering flaps 6 cardinally installed in the main-space-rocket 2 upper part. Currently all four flaps 6 are vertically set and are entirely inside the space-rocket fuselage. They are set this way during the space-rocket ascent toward space. Here the arrows show the deflection out directions of the flaps 6. Whereas FIG. 104 is the side view, FIG. 105 is the top view, FIG. 106 is the front view. All four flaps 6 are in large sizes so that they could steer the space-rockets even at low speeds of their descent in the Earth's atmosphere. Each space-rocket has cardinally installed four steering flaps 6. Two opposite flaps 6 have additionally rotary installed some torsional-triangles 59 which serve for precise steering of entire space-rocket axial torsion, needed before landing on two deck-gantries 20.

FIG. 107, 108, 109 show three views of four steering flaps 6 in the main-space-rocket 2 upper part. Currently all four flaps 6 are a lot deflected outside ergo mainly for steering the space-rocket at average speed of its descent in the Earth's atmosphere like on FIG. 215-216. And FIG. 107 is the side view, FIG. 108 is the top view, FIG. 109 is the front view. On current views the arrows show the possible deflection out directions of the flaps 6. Moreover on FIG. 109 two torsional-triangles 59 are sketched in a few settings varies twisted.

FIG. 110, 111, 112 show three views of four steering flaps 6 in the main-space-rocket 2 upper part. Currently all four flaps 6 are entirely deflected outside ergo mainly for aerodynamic braking and steering the space-rocket at low speed of its descent in the Earth's atmosphere like on FIG. 262-267. And FIG. 110 is the side view, FIG. 111 is the top view, FIG. 112 is the front view. On current views the arrows show the return direction of flaps 6. Moreover here the torsional-triangles 59 are also sketched in a few settings varied twisted. The views on FIG. 104-112 show also four deflection mechanisms of the flaps 6. Each such deflection mechanism consists of one linear-actuator 60 and of two ample-brackets 57. The linear-actuators 60 steer deflections of the flaps 6 whilst the ample-brackets 57 are subsidiary. These ample-brackets 57 are not marked on current views but only on next FIG. 113-118. On current top views the deflection mechanisms are in fullness visible. Whilst the side views and the front views contain both the views and the sketches of the deflection mechanisms.

FIG. 113, 114, 115, 116, 117, 118 show the enlarged views of one steering flap 6 together with the sketches of its deflection mechanism in the main-space-rocket 2 fragment.

And FIG. 113-115 show three enlarged views of one steering flap 6 which is vertically set and entirely inside the space-rocket fuselage. Whereas FIG. 113 is the side view, FIG. 114 is the top view, FIG. 115 is the front view. On FIG. 113 the arrows show direction of deflection out of the flap 6. And FIG. 116-118 show three enlarged views of one flap 6 which is entirely deflected outside the space-rocket fuselage. Whereas FIG. 116 is the side view, FIG. 117 is the top view, FIG. 118 is the front view. Moreover here one torsional-triangle 59 is sketched in several variously twisted settings. Each deflection mechanism of the flap 6 consists of one linear-actuator 60 and of two ample-brackets 57. Each flap 6 is cardinally installed by means of hinges to the space-rocket fuselage. Each flap 6 has permanently fastened two ample-brackets 57 whereto are rotatably installed the linear-actuator 60. The linear-actuator 60 second end is rotatably installed inside the space-rocket fuselage. The linear-actuators 60 steer deflections of the entire flaps 6. On upper parts of two opposite flaps 6 are installed rotary-actuators 58 which strongly grasp and steer axial torsion of the torsional-triangles 59. Therewith both torsional-triangles 59 serve for precise steering of entire space-rocket axial torsion, needed before landing on two deck-gantries 20. The torsional-triangles 59 can be rotary installed on all four flaps 6. The torsional-triangles 59 are triangular so that they could be used at all speeds and stages of the space-rocket descent in the Earth's atmosphere. During the first time period of the space-rocket descent in the Earth's atmosphere occur gigantic pushing forces on all flaps 6 and on both torsional-triangles 59 which are shown on further FIG. 212-214.

FIG. 119, 120, 121 show three views of the fragment of one main-space-rocket 2 upper part which has entirely lowered down all ten spreadable-arms 5 and consequently they are alongside the space-rocket fuselage. Whereas FIG. 119 is the side view. And FIG. 120 is the top view which is in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. And FIG. 121 is the front view. Whereas FIG. 119 shows only the sub-assemblies outside the space-rocket fuselage. Here is visible that all ten spreadable-arms 5 are suitably spaced out in the space-rocket fuselage so that they all could spread out on two sides. Furthermore it is visible that each spreadable-arm 5 consists of two lateral-beams 56 and one middle-beam 55 with permanently fastened a long-plate 64. The middle-beam 55 bottom is rotatably joined with a slider 53. Whereat the middle-beam 55 top is rotatably joined with the bottoms of both lateral-beams 56. Whilst both lateral-beams 56 tops are rotatably joined with the space-rocket fuselage. Furthermore, both lateral-beams 56 tops are bent and are inside the space-rocket fuselage. These lateral-beams 56 bent parts are transverse to the space-rocket fuselage. These lateral-beams 56 bent parts are very near to moving mechanism which moves this entire spreadable-arm 5. It is visible on FIG. 120 and there simultaneously it is visible that these moving mechanisms do not overlap and collide with each other during moving. This FIG. 120 shows the moving mechanisms outside and inside space-rocket. These views show in this space-rocket interior, arrangement of ten moving mechanisms which spread out the spreadable-arms 5.

Furthermore above each spreadable-arm 5 moving mechanism is installed a pushing mechanism having a blocking-bar 54 which serves for blocking the middle-beam 55 in spreadable-arm 5 whilst it is entirely lifted upward. This pushing mechanism consists of the large-C-profile 69, a linear-actuator 70 and of a vertical-low-bar 71. Here is shown in the space-rocket interior, the arrangement of ten large-C-profiles 69 which have inside the blocking-bars 54 which are moved slidingly and lineally by linear-actuators 70. And FIG. 121 is the fragment front view of one main-space-rocket 2 upper part. This view shows only the sub-assemblies outside the space-rocket fuselage. Here outside the space-rocket fuselage is visible in what way are spaced out all ten spreadable-arms 5. On all views FIG. 119-121, all blocking-bars 54 are entirely inside the space-rocket fuselage. Thus each blocking-bar 54 is situated in the large-C-profile 69.

FIG. 122, 123 show two views of the fragment of one main-space-rocket 2 upper part which has entirely lifted upward all ten spreadable-arms 5 and consequently they are completely spread out on two sides. And therefor these spreadable-arms 5 are transverse the space-rocket fuselage. Whereas FIG. 122 is the side view. And FIG. 123 is the top view. And FIG. 122 shows only the sub-assemblies outside the space-rocket fuselage. Here outside the space-rocket fuselage is visible in what way are spaced out all ten spreadable-arms 5 after their lifting upward. Furthermore here are clearly visible the whole corner-beams 52 on space-rocket fuselage because all spreadable-arms 5 are lifted upward. Two corner-beams 52 serve for leading one slider 53. And FIG. 123 is the top view and shows the sub-assemblies outside and inside the space-rocket fuselage after lifting upward all ten spreadable-arms 5. Here is visible that all ten spreadable-arms 5 are suitably spaced out in the space-rocket fuselage so that they all could spread out on two sides. Furthermore is visible in the space-rocket interior, arrangement of ten moving mechanisms which spread out ten spreadable-arms 5. And is visible in the space-rocket interior, arrangement of ten large-C-profiles 69 wherein inside are the blocking-bars 54 which can be move slidingly and lineally by linear-actuators 70. Currently all blocking-bars 54 are entirely slid outside the space-rocket fuselage and it entirely blocked all middle-beams 55 in all spreadable-arms 5. Whilst the lateral-beams 56 upper bent parts are inside the space-rocket fuselage and currently are alongside the space-rocket fuselage. And consequently they are very near to moving mechanisms which spread out the entire spreadable-arms 5. They are better visible on further FIG. 150, 153, 154, 156. On current FIG. 123 it is visible that all lateral-beams 56 bent parts do not collide with themselves during moving. There are also visible some half empty interiors of all ten large-C-profiles 69 because all ten blocking-bars 54 half-lengths moved slidingly and lineally outside the space-rocket fuselage. Here are also marked the long-plate 64 and the sliders 53. Current FIG. 122-123 are similar to earlier FIG. 102-103.

FIG. 124, 125 show two enlarged views of the fragment of one booster-space-rocket 1 upper part which has entirely lifted upward all six spreadable-arms 5 and consequently they are completely spread out on two sides. And therefor these spreadable-arms 5 are transverse the space-rocket fuselage. And FIG. 124 is the side view, FIG. 125 is the top view. And FIG. 124 shows only the sub-assemblies outside the space-rocket fuselage. Here outside the space-rocket fuselage is visible in what way are spaced out all six spreadable-arms 5 after their lift upward. And FIG. 125 shows the sub-assemblies outside and inside space-rocket after lifting upward all six spreadable-arms 5. Here is visible that all six spreadable-arms 5 are suitably spaced out in the space-rocket fuselage so that they all could spread out on two sides. Furthermore all views show in the space-rocket interior, arrangement of six moving mechanisms of six spreadable-arms 5. And show in the space-rocket interior, arrangement of six large-C-profiles 69 wherein inside are the blocking-bars 54 which can be move slidingly and lineally by linear-actuators 70. Now all blocking-bars 54 are entirely slid outside the space-rocket fuselage and it entirely blocked all middle-beams 55 in all spreadable-arms 5. There are visible the half empty interiors of all six large-C-profiles 69 because all six blocking-bars 54 half-lengths moved slidingly and lineally outside the space-rocket fuselage. Here are marked also the long-plates 64, the sliders 53 and the corner-beams 52 on space-rocket fuselage. Current FIG. 124-125 are similar to previous FIG. 122-123, FIG. 100-101.

FIG. 126, 127, 128 show three views of one entire spreadable-arm 5 together with its moving mechanism and with one blocking-bar 54 and its pushing mechanism. These views are in the space-rocket fuselage fragments with the sub-assemblies outside and inside. This spreadable-arm 5 is entirely lowered down to P1 first setting and consequently it is alongside the space-rocket fuselage. Whilst the blocking-bar 54 is inside the space-rocket fuselage. And FIG. 126 is the side view with the partial vertical sectional view. And FIG. 127 is the top view in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. FIG. 127 is the view only of the components situated upwards of the common-long-axle 65. And FIG. 128 is the front view but only of the sub-assemblies outside the space-rocket. Furthermore here are auxiliary one sectional view and the bottom projection both without some drawing numbers. On FIG. 126 the arrows show the moving directions of the spreadable-arm 5 components. And the arrows show the moving direction of the blocking-bar 54. Here is also visible the fragment of a pressure-tank 61 inside the space-rocket fuselage. It shows and explains that all mechanisms are designed in such way that they fit into vacant space above this pressure-tank 61.

Each spreadable-arm 5 mainly consists of two lateral-beams 56 and one middle-beam 55 which are joined in suitable way with themselves and with the additional components. Both lateral-beams 56 bottoms are rotatably joined with the middle-beam 55 top by means of the common-long-axle 65. Between the middle-beam 55 and both lateral-beams 56 on common-long-axle 65 are inserted two distance-blocks 81. The middle-beam 55 bottom is rotatably joined with the slider 53 by means of the holding-axle 66. The slider 53 can move slidingly between two corner-beams 52 on space-rocket fuselage. To middle-beam 55 is permanently fastened a T-bar 67 and the long-plate 64 for aerodynamic purposes. Inside the middle-beam 55 bottom is installed a frictional-brake 68. Whereat, both lateral-beams 56 tops are rotatably joined with the space-rocket fuselage by means of two bearing-axles 63 which are situated in four bearing-brackets 80. Both lateral-beams 56 have upper bent parts and which are situated inside the space-rocket fuselage. To each upper bent part are permanently fastened two flat-bars 72 which have some oval-openings. In current setting, both lateral-beams 56 upper bent parts with all flat-bars 72 are transverse the space-rocket fuselage. These lateral-beams 56 bent parts are very near the moving mechanism which spreads out the entire spreadable-arm 5. Here is also shown that above each spreadable-arm 5 moving mechanism is installed the pushing mechanism of the blocking-bar 54. This pushing mechanism consists of the large-C-profile 69, a linear-actuator 70 and of a vertical-low-bar 71. Currently the entire blocking-bar 54 is inside the large-C-profile 69 and consequently it is inside the space-rocket fuselage.

FIG. 129, 130, 131 show three enlarged views of the FIG. 126, 127, 128 fragments. Whereas FIG. 129 is the side view with the partial vertical sectional view. And FIG. 130 is the top view in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. And FIG. 131 is the front view but only of the sub-assemblies outside the space-rocket fuselage. On these FIG. 129, 130, 131 are already more clearly visible the moving mechanism components of one spreadable-arm 5. These are following components and sub-assemblies; one servomotor 73, two worm-gears 74, one common-roller 78, two threaded-pipes 75, two special-nuts 76, two cylindrical-pegs 77 and two bearing-seats 79. Furthermore here are better visible both bearing-axles 63 and four bearing-brackets 80. On FIG. 129 the arrows show the moving directions of the lateral-beams 56 upper bent parts which are inside the space-rocket fuselage. And together with them move the flat-bars 72 which have the oval-openings. Here is also better visible the pushing mechanism of the blocking-bar 54. This pushing mechanism consists of the large-C-profile 69, the linear-actuator 70 and of the vertical-low-bar 71. Now the entire blocking-bar 54 is inside the large-C-profile 69 and consequently is inside the space-rocket fuselage. The blocking-bar 54 is situated and move slidingly and lineally inside the large-C-profile 69. The blocking-bar 54 is the same long like the large-C-profile 69. The blocking-bar 54 with its half total length can slide outside the space-rocket fuselage and it is visible on following FIGS. 150-157 and 178-179. The blocking-bar 54 has in its bottom-surface a key-seat which is shaped like a T-groove and which is fitted with the T-bar 67 on middle-beam 55. Above the large-C-profile 69 is permanently fastened the linear-actuator 70. This linear-actuator 70 is permanently joined with the blocking-bar 54 by means of the vertical-low-bar 71. Consequently the linear-actuator 70 serves for pushing the blocking-bar 54 outside the space-rocket fuselage and pulling it back. Whilst the spreadable-arm 5 is entirely lifted up and after sliding outside the blocking-bar 54 then its T-groove enters into T-bar 67 on middle-beam 55. The blocking-bar 54 serves for blocking in all directions the middle-beam 55 whilst it is entirely lifted upward to P6 setting.

The middle-beam 55 after its blocking gains possibility of carrying burdens in all directions. Consequently the middle-beam 55 after its blocking carries burdens together with both lateral-beams 56. It significantly influences upon full-load capacity of one spreadable-arm 5. The middle-beam 55 blocking causes also strengthening of the entire spreadable-arm 5 in all directions.

Burdens upon every spreadable-arm 5 will occur during the space-rocket descent in the Earth's atmosphere and during the space-rocket hanging itself on two damping-wagons 30 or 31. All blocking-bars 54 can also be slide outside space-rockets whilst the spreadable-arms 5 are not entirely lifted upward. Such situation can be favorable during the first time period of the space-rocket descent in the Earth's atmosphere and which is shown on FIGS. 212A, B and 214A, B. During giant speed of the space-rocket descent in the Earth's atmosphere slid outside all blocking-bars 54 will cause some aerodynamic braking which will stabilize this space-rocket descent. Further description of the current views are the same like previous FIG. 126, 127, 128 and therefor are not fully quoted here.

FIG. 132, 133, 134 show three very enlarged fragments of previous FIG. 129, 130, 131. And current FIG. 132 is the side view with the partial vertical sectional view. And FIG. 133 is the top view. And FIG. 134 is the front view but only of the sub-assemblies outside the space-rocket and the sketches of four limiters 62 in the space-rocket interior. The front view of alone moving mechanism of the spreadable-arm 5 is on next FIG. 137. All current views, show in the most detail way the entire moving mechanism construction of the spreadable-arm 5 in the space-rocket fuselage fragment. Thereby, there is well visible the servomotor 73 which by means of the common-roller 78 propels two wormgear 74 which rotate two threaded-pipes 75 and whereon move two special-nuts 76 with the cylindrical-pegs 77. Both threaded-pipes 75 tops are rotatably installed by means of two bearing-seats 79. Both lateral-beams 56 upper bent parts have permanently fastened the flat-bars 72 which have the oval-openings. These are best visible on further FIG. 141-143. Such solution is necessary so that the spreadable-arm 5 entire moving mechanism would require the least space above the pressure-tank 61. In the flat-bars 72 oval-openings can move slidingly the cylindrical-pegs 77. Whereas at the same time each entire special-nut 76 move slidingly and tightly between two flat-bars 72. This entire moving mechanism by means of two cylindrical-pegs 77 push all flat-bars 72 and consequently both lateral-beams 56 upper bent parts and it consequently moves the entire spreadable-arm 5. The spreadable-arm 5 entire moving mechanism is driven with one servomotor 73 so that both lateral-beams 56 would slant always equally out. Both lateral-beams 56 are rotatably installed to the space-rocket fuselage by means of the bearing-axles 63. Each bearing-axle 63 is upbeared to the space-rocket fuselage by means of two bearing-brackets 80. There are also four limiters 62 permanently fastened inside the space-rocket fuselage. On limiters 62 will lean against all flat-bars 72 whilst the entire spreadable-arm 5 will be entirely lifted up to P6 setting. Between two lateral-beams 56 upper bent parts is situated the pushing mechanism of blocking-bar 54 that was earlier exactly described. Further description of the current views are the same like previous FIG. 126-131 and therefor are not fully quoted here.

FIG. 135, 136, 137 show three enlarged views of the alone entire moving mechanism of one spreadable-arm 5 together with the fragments of two lateral-beams 56 of the spreadable-arm 5 in P1 setting. And FIG. 135 is the side view, FIG. 136 is the top view, FIG. 137 is the front view. Here are not any space-rocket fragments except of four limiters 62. Here are also visible the limiters 62 whereon will lean against the flat-bars 72 whilst the entire spreadable-arm 5 will be entirely lifted up to P6 setting. All these views show in most detail way the entire moving mechanism construction of one spreadable-arm 5. Further description of this moving mechanism construction of one spreadable-arm 5 is in previous FIG. 132-134.

FIG. 138, 139, 140 show three enlarged views of one alone moving mechanism components of one spreadable-arm 5. On these views are very well visible all components of this moving mechanism which were described in previous FIGs. Whereas FIG. 138 is the side view, FIG. 139 is the top view, FIG. 138 is the front view. This FIG. 138 shows also for example two sketches of one special-nut 76 with the cylindrical-peg 77 in two locations on one threaded-pipe 75. These sketches show in what way the special-nuts 76 can move on threaded-pipes 75.

FIG. 141, 142, 143 show the enlarged views of four flat-bars 72 (having oval-openings) which are permanently fastened to both lateral-beams 56 upper bent parts. These views are related to FIG. 138-140.

FIG. 144, 145, 146 show outside and partly inside the space-rocket fragment, the three views of one entire spreadable-arm 5 in P2 setting which is in one-quarter lifted upward and consequently protrudes outside the space-rocket fuselage. Whereas FIG. 144 is the side view and the partial vertical sectional view of the space-rocket fuselage. And FIG. 145 is the top view. And FIG. 146 is the front view but only outside the space-rocket fuselage. This FIG. 146 has also an auxiliary bottom projection without some drawing number. On FIG. 144 are also sketched intermediate settings of the spreadable-arm 5, it means in P3, P4 and P5 settings. There is also marked P6 final setting thus whilst the spreadable-arm 5 is entirely lifted upward. Here the arrows show the spreading direction of this spreadable-arm 5 from its P1 first setting up to its last P6 setting. Inside the space-rocket fragment FIG. 144 shows all components and moving mechanism of the spreadable-arm 5. The lateral-beams 56 upper bent parts with the flat-bars 72 are in P2 setting and are also sketched in P3 setting. There is also the pressure-tank 61 fragment in the space-rocket interior and it shows and explain that the flat-bars 72 during their moving do not hook with this pressure-tank 61. On space-rocket fuselage one large arrow shows the space-rocket descent direction in the Earth's atmosphere whilst the external arrows show from what direction comes flying atmospheric air and consequently in what way this air strongly crowds into spreadable-arm 5 in P2, P3, P4 and P5 settings. Currently the entire blocking-bar 54 is inside the space-rocket fuselage. Here are visible a lot the components mentioned in FIG. 126, 127, 128. Here and on several next FIGs. the lateral-beams 56 ends and the middle-beams 55 ends are marked with crossed lines like a X letter so that those ends would be better visible.

FIG. 147, 148, 149 show three enlarged fragments of previous FIG. 144, 145, 146. Current views show the upper part of the spreadable-arm 5 in P2 setting. And FIG. 147 is the side view and the partial vertical sectional view of the space-rocket fuselage. Here is visible the pressure-tank 61 fragment inside the space-rocket fuselage. And FIG. 148 is the top view and here are visible some subjacent components which are not visible on fragments FIG. 147, 149. And FIG. 149 is the front view but only of the sub-assemblies outside the space-rocket. All current views show in the most detail way surrounding of the flat-bars 72 with the lateral-beams 56 upper bent parts in P2 setting in relation to spreadable-arm 5 all moving mechanism components. Here is visible way of acting of one spreadable-arm 5 entire moving mechanism. The servomotor 73 propelled the common-roller 78 whereby propelled two worm-gears 74 and they caused rotation of both threaded-pipes 75. It then caused that both special-nuts 76 with both cylindrical-pegs 77 moved down on these both threaded-pipes 75. Hence both cylindrical-pegs 77 pushed down all flat-bars 72 together with both lateral-beams 56 upper bent parts and it caused that the entire spreadable-arm 5 rose upward outside the space-rocket fuselage. During moving down of both special-nuts 76 their both cylindrical-pegs 77 move slidingly in the flat-bars 72 oval-openings. On FIG. 147 are also visible the limiters 62 whereon will lean against the flat-bars 72 whilst the entire spreadable-arm 5 will be entirely lifted upward to P6 setting. It is shown on next FIG. 150-157. Here is also the linear-actuator 70 which moves slidingly the blocking-bar 54 inside the large-C-profile 69. Currently the blocking-bar 54 is entirely inside the space-rocket fuselage.

FIG. 150, 151, 152, 153 show outside and inside the space-rocket fragment the views of one entire spreadable-arm 5 in the P6 setting which is entirely lifted upward and consequently it is transverse the space-rocket fuselage. Whereat the blocking-bar 54 is slid maximally outside the space-rocket fuselage and it entirely blocked the middle-beam 55 in the spreadable-arm 5. And FIG. 150 is the side view with partial vertical sectional view of the space-rocket fuselage. And FIG. 151 is the top view and with all components and mechanisms and this view has one auxiliary right-side-view without some drawing number. And FIG. 152 is the front view outside the space-rocket fuselage. This view in the space-rocket interior has the sketches of the flat-bars 72 together with both lateral-beams 56 upper bent parts. On space-rocket fuselage are visible two whole corner-beams 52 which lead the slider 53 of the spreadable-arm 5. This view has also the auxiliary bottom projection without some drawing number. On FIG. 150 on space-rocket fuselage one large arrow shows the space-rocket descent direction in the Earth's atmosphere. Whereas the external arrows show from what direction comes flying atmospheric air and consequently in what way this air strongly crowds into the spreadable-arm 5 entirely lifted upward. FIG. 153 is auxiliary and is the side view and the partial vertical sectional view which shows FIG. 152 only in the middle. Namely FIG. 153 shows the fragments of the middle-beam 55 and of the slider 53 and furthermore of the blocking-bar 54 fragment. All views show that the flat-bars 72 together with the lateral-beams 56 upper bent parts are directed down inside the space-rocket fuselage and consequently are alongside of the space-rocket fuselage. On FIG. 150 is well visible that all flat-bars 72 are leaned against on limiters 62 in the space-rocket fuselage. The blocking-bar 54 is slid maximally outside the space-rocket fuselage and it entirely blocked the middle-beam 55 in the spreadable-arm 5. There is visible an empty part of the large-C-profile 69 because the blocking-bar 54 moved slidingly and lineally outside. Whereas the linear-actuator 70 is folded entirely up. The middle-beam 55 after its blocking gains possibility of carrying burdens in all directions. Possibility of carrying burdens by this middle-beam 55 is very favorable for the entire spreadable-arm 5. During aerodynamic braking and during hanging of the space-rocket on two damping-wagons 30 or 31, all spreadable-arms 5 will be maximally burden. Recommended is therefor so that all middle-beams 55 would carry also burdens together with all lateral-beams 56. Current views descriptions are tied with descriptions of the pushing mechanism of the blocking-bar 54 in earlier FIG. 129-131.

FIG. 154, 155, 156, 157 show the enlarged fragments of earlier FIG. 150-153. Whereas FIG. 154 is the side view, FIG. 155 is the top view And FIG. 156 is the front view, FIG. 157 is auxiliary and is the side view and the partial vertical sectional view which shows FIG. 156 only in the middle. Whereat on current FIG. 155 are visible some subjacent components which are not visible on FIG. 154, 156. Current views descriptions are the same like descriptions of previous FIG. 150-153 and descriptions of the pushing mechanism of the blocking-bar 54 on earlier FIG. 129-131. On current views are more clearly visible the blocking-bar 54 with the T-groove, the large-C-profile 69, the vertical-low-bar 71, the linear-actuator 70 and the middle-beam 55 with the T-bar 67.

FIG. 158, 159, 160 show three views of the alone spreadable-arm 5 which is entirely lowered down ergo it is in P1 setting. These views are similar to FIG. 126, 127, 128 however do not contain the moving mechanism of this spreadable-arm 5 except of the cylindrical-pegs 77. There are also not the space-rocket fuselage fragments except of four bearing-brackets 80 and four limiters 62. Whilst here is also the entire pushing mechanism of the blocking-bar 54 which is not slid outside. And FIG. 158 is the side view and here the arrows show the moving directions of the spreadable-arm 5 components and of the blocking-bar 54. And FIG. 159 is the top view, FIG. 160 is the front view together with five auxiliary horizontal sectional views and with one bottom projection, all without drawing numbers. All views show that each such spreadable-arm 5 mainly consists of two lateral-beams 56 and of one middle-beam 55. Both lateral-beams 56 are bent in the upper part and are rotatably installed to the space-rocket fuselage by means of two bearing-axles 63. Both lateral-beams 56 upper bent parts have permanently fastened the flat-bars 72 having the oval-openings. Both lateral-beams 56 are subsidiarily permanently fastened with themselves by means of two plates without some numbers. Whereat each bearing-axle 63 is upbeared to the space-rocket fuselage by means of two bearing-brackets 80. Both lateral-beams 56 are rotatably joined by one common-long-axle 65 with the middle-beam 55. On common-long-axle 65 are also two distance-blocks 81 which are between the middle-beam 55 and each lateral-beam 56. On middle-beam 55 upper part is permanently fastened the long-plate 64 for aerodynamic purposes. In the middle-beam 55 bottom is permanently fastened the T-bar 67. In the middle-beam 55 bottom is rotatably installed the slider 53 by means of the holding-axle 66. Furthermore, inside the middle-beam 55 bottom is installed the frictional-brake 68.

FIG. 161, 162, 163 show three enlarged fragments of FIG. 158, 159, 160. And FIG. 161 is the side view, FIG. 162 is the top view, FIG. 163 is the front view together with five auxiliary horizontal sectional views and with one bottom projection. Current views descriptions are the same like descriptions of previous FIG. 158-160. Here are more clearly visible all smaller components as the vertical-low-bar 71, the T-bar 67, the slider 53, the frictional-brake 68. Furthermore in the blocking-bar 54 is visible the T-groove.

FIG. 164, 165, 166 show three views of the alone spreadable-arm 5 which is in one-quarter lifted up to P2 setting. These views are similar to FIG. 144, 145, 146 however do not contain the moving mechanism of this spreadable-arm 5 except of the cylindrical-pegs 77. There are also not the space-rocket fragments except of four bearing-brackets 80 and four limiters 62. Whilst here is also the entire pushing mechanism of the blocking-bar 54 that is not slid outside. And FIG. 164 is the side view and here is visible in what way stoop down the lateral-beams 56 upper bent parts and together with them stoop down the flat-bars 72 which have the oval-openings. Here the arrows show the directions of further moving of the spreadable-arm 5 components and of the blocking-bar 54. And FIG. 165 is the top view, FIG. 166 is the front view.

FIG. 167, 168, 169 show the three enlarged fragments of FIG. 164, 165, 166. Whereas FIG. 167 is the side view, FIG. 168 is the top view, FIG. 169 is the front view. Current views descriptions are the same like descriptions of previous FIG. 164, 165, 166. Here are better visible all smaller components. Furthermore in the blocking-bar 54 is visible the T-groove.

FIG. 170, 171, 172 are the three views of the alone spreadable-arm 5 together with the entire pushing mechanism of the blocking-bar 54 which is not slid outside whilst the arrows show its sliding direction and range. The spreadable-arm 5 is entirely lifted up to P6 setting. And FIG. 170 is the side view, FIG. 171 is the top view, FIG. 172 is the front view. Current views do not contain the moving mechanism of the spreadable-arm 5 except the cylindrical-pegs 77. Current views are in the same arrangement like previous FIG. 150-153 yet here are not any space-rocket fragments except four bearing-brackets 80 and four limiters 62.

FIG. 173, 174, 175 are the three views of the alone middle-beam 55 together with entire pushing mechanism of the blocking-bar 54 that is not slid outside whilst arrows show its sliding direction and range. The middle-beam 55 is entirely lifted upward to P6 setting like on previous FIG. 170-172. And FIG. 173 is the side view, FIG. 174 is the top view, FIG. 175 is the front view.

FIG. 176 is the side view of the alone middle-beam 55 together with the entire pushing mechanism of the blocking-bar 54. Here the blocking-bar 54 is slid very little outside to location where it will soon begin to slip into T-bar 67 which is permanently fastened to middle-beam 55.

FIG. 177 is the side view of the alone middle-beam 55 together with the entire pushing mechanism of the blocking-bar 54. Here the blocking-bar 54 is slid a lot outside and consequently is inserted already into T-bar 67 half length. Here is visible the empty part of the large-C-profile 69 because the blocking-bar 54 slid a lot outside.

FIG. 178, 179 are two views of the alone spreadable-arm 5 together with the entire pushing mechanism of the blocking-bar 54. And FIG. 178 is the side view, FIG. 179 is the top view. Here the blocking-bar 54 is maximally slid outside and consequently is already entirely inserted into T-bar 67. Here is visible the empty part of large-C-profile 69 because the blocking-bar 54 moved slidingly and lineally maximally outside. In maximally slid outside location the blocking-bar 54 fulfills its main purpose which is total blocking the middle-beam 55 in all directions. The middle-beam 55 after its blocking gains possibility of carrying burdens in all directions. Therefore the middle-beam 55 after its blocking carries burdens together with both lateral-beams 56. It significantly influences upon full-load capacity of one spreadable-arm 5. The middle-beam 55 blocking causes also strengthening of the entire spreadable-arm 5 in all directions. Burdens upon all spreadable-arms 5 will occur during the space-rocket descent in the Earth's atmosphere and during the space-rocket hanging itself on two damping-wagons 30 or 31. During the space-rocket descent in atmosphere it will maneuver which will cause strong torsional forces on all spreadable-arms 5. Although the most important is that the middle-beam 55 after its blocking gains upward carrying capacity which is necessary during the space-rocket hanging itself on two damping-wagons 30 or 31. Hence, the middle-beam 55 blocking by blocking-bar 54 is very important for each spreadable-arm 5.

FIG. 180, 181, 182 show the enlarged fragments of FIG. 170, 171, 172 in the same arrangement. And FIG. 180 is the side view, FIG. 181 is the top view, FIG. 182 is the front view.

FIG. 183, 184, 185 show the enlarged fragments of FIG. 173, 174, 175 in the same arrangement. And FIG. 183 is the side view, FIG. 184 is the top view, FIG. 185 is the front view.

FIG. 186 is the side view and shows the enlarged fragment of FIG. 176 in the same setting.

FIG. 187 is the top view and shows the enlarged fragments of FIG. 177 in the same setting.

FIG. 188, 189, 190, 191 show the views of the frictional-brake 68 installed inside the middle-beam 55 bottom together with the slider 53. One frictional-brake 68 consists of one brake-block 82 and of one linear-actuator 83. On all views this frictional-brake 68 is sketched because it is inside the middle-beam 55 bottom. And FIG. 188 is the side view, FIG. 189 is the top view, FIG. 190 is the front view. On these views the middle-beam 55 is vertically set ergo it is in P1 setting. And FIG. 191 is side view of the alone middle-beam 55 bottom which is slanted to P6 full setting. On all views is visible the slider 53 which has the sideward protrusive part and wherein is situated the holding-axle 66. In the middle-beam 55 bottom are permanently fastened two ending-brackets 84 with the holes. Here is also visible the T-bar 67 permanently fastened to middle-beam 55. All views display mutual setting of the brake-block 82, the linear-actuator 83, the slider 53 and of the holding-axle 66. And on all views, the arrows show the moving direction of the brake-block 82. The brake-block 82 pressure on sideward protrusive part of the slider 53 will brake its rotation against the middle-beam 55. The whole frictional-brake 68 is supposed to enable blocking this rotation which will step-by-step immobilize the slider 53 between two corner-beams 52 on space-rocket fuselage. Whilst the holding-axle 66 fulfills here only guiding function. Step-by-step immobilizing of the slider 53 by frictional-brake 68 will step-by-step immobilize the spreadable-arm 5 bottom. Step-by-step immobilizing of all spreadable-arms 5 bottoms will be necessary during the space-rocket descent in the Earth's atmosphere. The frictional-brake 68 fulfills subsidiary function because the entire spreadable-arm 5 will be lifted upward and set to suitable setting by its moving mechanism which contains in itself also blocking function and braking function.

FIG. 192, 193, 194, 195 show the views of one sliding-engines-cover 7 that can be lowered down and here is in version flat underneath after its lowering down. The sliding-engines-cover 7 is installed to the space-rocket fuselage bottom because there are its main engines. All current views show only the booster-space-rocket 1 bottom. Currently the sliding-engines-cover 7 is entirely lifted up and it causes that all main engines nozzles 85 are entirely uncovered. And FIG. 192 is the side view. And FIG. 193 is the top view only of the current space-rocket fragment. And FIG. 194 is the front view. And FIG. 195 is the bottom projection of FIG. 192 and that mean of the current space-rocket bottom in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the above views. The whole sliding-engines-cover 7 consists of a main-cover having two sliding jalousies 88 and consists of two sliding rounded-plates 91. The main-cover with two jalousies 88 consists of four flat carrying-plates 86, two long U-form-rails 87, two stiffening-beams 92, two jalousies 88 wherewith each is joined by hinges with one side-plate 89. Whereas each rounded-plate 91 slides in two angle-profiles 90. The main-cover with jalousies 88 is installed to the space-rocket fuselage by means of four flat carrying-plates 86. All flat carrying-plates 86 are permanently fastened to this space-rocket fuselage and are perpendicular to this space-rocket fuselage. To carrying-plates 86 opposite sides are permanently fastened two U-form-rails 87. These two U-form-rails 87 are long and are installed on space-rocket fuselage opposite sides. Each long U-form-rail 87 is permanently fastened to two carrying-plates 86. Thereby both long U-form-rails 87 stretch on from the space-rocket fuselage one side to its bottom and further to the space-rocket fuselage opposite side. Consequently each long U-form-rail 87 reminds with its shape an extensive U letter. The opposite U-form-rails 87 upper ends are permanently fastened with themselves and with the space-rocket fuselage by means of the stiffening-beam 92. Together there are two stiffening-beams 92. In both U-form-rails 87 are placed two jalousies 88 wherewith each one is joined by hinges with one side-plate 89. These both jalousies 88 with the side-plates 89 are placed on two opposite sides of the space-rocket fuselage. These both jalousies 88 with the side-plates 89 can move slidingly in two U-form-rails 87. As result of their sliding down, they will slide to U-form-rails 87 bottom part. Then both jalousies 88 will come to each other and touch on themselves in the U-form-rails 87 bottom and in their middle. During moving down of both jalousies 88, there will move slidingly down also both side-plates 89 which will remain in the vertical part of U-form-rails 87. And as result, underneath the space-rocket arose a square flat surface after coming to each other and touching on themselves of both jalousies 88. This square flat surface will cover the main engines underneath. This flat underneath surface is the main-cover with jalousies 88 of the space-rocket main engines whereas this space-rocket enters into the Earth's atmosphere.

Furthermore to the space-rocket fuselage are installed two rounded-plates 91 which are situated on two opposite sides of the space-rocket fuselage that mean sides which does not cover in fullness the main-cover with jalousies 88. Each rounded-plate 91 slides in two two angle-profiles 90. All four angle-profiles 90 are permanently fastened to the space-rocket fuselage. In two angle-profiles 90 is placed one sliding rounded-plate 91 which can move slidingly down and up in these two angle-profiles 90. Both sliding rounded-plates 91 after their lowering down shield almost entirely the main engines on the both sides which are not entirely covered by main-cover with jalousies 88. Consequently both sliding rounded-plates 91 are some extensive side shields of the main engines. On all views, the arrows show the sliding directions of both jalousies 88 with the side-plates 89 and of both rounded-plates 91. The sliding-engines-cover 7 will be lifted entirely upward during running the space-rocket main engines ergo during the space-rocket liftoff and during braking action at space-rocket landing. Both jalousies 88 can be very easy and quickly replace with a new one after each space-rocket landing. On FIGS. 193 and 195 are visible airy spaces between the space-rocket fuselage and the sliding-engines-cover 7 all components. Throughout these airy spaces can freely breeze air. These airy spaces for air cause that during the space-rocket liftoff there will not be some aerodynamic braking caused by sliding-engines-cover 7. Shown here the solution of the sliding-engines-cover 7 does not contain some sliding mechanisms of the jalousies 88 and of the rounded-plates 91. These mechanisms can be made according to some known solutions.

FIG. 196, 197, 198, 199 show the views of one sliding-engines-cover 7 that can be lowered down and here is in version flat underneath after its lowering down. The sliding-engines-cover 7 is installed to the space-rocket fuselage bottom because there are its main engines. All current views show only the booster-space-rocket 1 bottom. Currently this sliding-engines-cover 7 is entirely lowered down and it causes that the space-rocket bottom is entirely covered underneath and almost entirely at both sides. And FIG. 196 is the side view, FIG. 197 is the top view only of the current space-rocket fragment, FIG. 198 is the front view, FIG. 199 is the bottom projection of FIG. 196 and that mean of the current space-rocket bottom in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the above views. On these projections are visible that both jalousies 88 came to each other and touched on themselves in the U-form-rails 87 bottom and in their middle. Whereat on FIGS. 196 and 198 are visible that both rounded-plates 91 are entirely lowered down until both jalousies 88. Here are also visible all components mentioned in description of previous FIG. 192-195. The sliding-engines-cover 7 will be lowered rapidly and entirely down before the space-rocket entry into the Earth's atmosphere. It will cover all space-rocket main-engines against some air hit and becoming overheated. Thereafter the sliding-engines-cover 7 will remain shut down during the space-rocket further descent in the Earth's atmosphere until the moment whilst it will be necessary the main engines firing blast for braking action at space-rocket landing. Lift upward of the sliding-engines-cover 7 can occur rapidly quickly.

FIG. 200, 201, 202, 203 show the views of the sliding-engines-cover 7 which can be lowered down and here is in version flat underneath after its lowering down. The sliding-engines-cover 7 is installed to the space-rocket fuselage bottom because there are its main engines. All current views show only the booster-space-rocket 1 bottom. On FIG. 200-201 the sliding-engines-cover 7 is entirely lifted up and the exhaust-fumes 9 gush down of all main engines nozzles 85. Whereas FIG. 200 is the side view. And FIG. 201 is the front view. Here is visible that all exhaust-fumes 9 gush down but beside both U-form-rails 87 and consequently they cannot melt them. Furthermore the U-form-rails 87 do not brake gushing down the exhaust-fumes 9 of all nozzles 85. Such space-rocket status will occur during the space-rocket liftoff and for beginning of the space-rocket descent from the Earth's orbit and later also at final phase for braking action at space-rocket landing. Whereat on FIG. 202-203 the sliding-engines-cover 7 is entirely lowered down and it causes that the space-rocket bottom is entirely covered. And FIG. 202 is the side view. And FIG. 203 is the front view. Such space-rocket status will occur during the space-rocket entering into the Earth's atmosphere and its further descent until the moment whilst there will be necessary the main engines firing blast for braking action at space-rocket landing. Lift upward of the sliding-engines-cover 7 can occur rapidly quickly. Here on space-rocket fuselage, the large arrows show the space-rocket descent direction in the Earth's atmosphere. Whereat the external arrows show from what direction comes flying atmospheric air and consequently in what way this air strongly crowds into both jalousies 88 which came to each other inside the U-form-rails 87. Whilst both rounded-plates 91 shield almost entirely at both sides the main-engines nozzles 85. Here are also visible the components mentioned in descriptions of FIG. 192-195.

FIG. 204, 205, 206, 207 show the views of one sliding-engines-cover 8 which can be lowered down and here is in version wedge-shaped underneath after its lowering down. This sliding-engines-cover 8 is installed to the space-rocket fuselage bottom because there are its main engines. All current views show only the booster-space-rocket 1 bottom. Currently the sliding-engines-cover 8 is entirely lifted upward and it causes that all main-engines nozzles 85 are entirely uncovered. Whereas FIG. 204 is the side view. And FIG. 205 is the top view only of the current space-rocket fragment. And FIG. 206 is the front view. And FIG. 207 is the bottom projection of the current space-rocket bottom in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the above views. This version of the sliding-engines-cover 8 is very similar in construction to version flat underneath shown on FIG. 192-195. Current version, the sliding-engines-cover 8 creates a wedge underneath the space-rocket after coming to each other and touching on themselves of both jalousies 88. This wedge underneath the space-rocket entirely cover underneath the space-rocket main engines. Furthermore both sliding rounded-plates 91 are pointed in some bottom edges so that they adjoin to both jalousies 88. Here in the space-rocket fuselage are different arrangements and kinds of the main engines nozzles 85 so that the exhaust-fumes 9 completely pass by U-form-rails 87. On all views, the arrows show the sliding directions of both jalousies 88 and both rounded-plates 91. Here is visible that the exhaust-fumes 9 gush down but beside both U-form-rails 87 and consequently they cannot melt them. Furthermore the U-form-rails 87 do not brake gushing down of the exhaust-fumes 9 of all nozzles 85. Here are also visible the components mentioned in description FIG. 192-195.

FIG. 208, 209, 210, 211 show the views of the sliding-engines-cover 8 which can be lowered down and here is in version wedge-shaped underneath after its lowering down. This sliding-engines-cover 8 is installed to the space-rocket fuselage bottom because there are its main engines. Current views show only the booster-space-rocket 1 bottom. On all views the sliding-engines-cover 8 is entirely lowered down and it causes that the space-rocket bottom is entirely covered. The views on FIG. 208, 209 show some main components emplacement of the sliding-engines-cover 8 in relation to themselves and with the components sketches which are veiled by some other members. And FIG. 208 is the side view, FIG. 209 is the front view. Whereat the views on FIG. 210-211 do not have the components sketches which are veiled by some other members. And FIG. 210 is the side view, FIG. 211 is the front view. These views show in what way this sliding-engines-cover 8 expands and divides in two sides some atmospheric air during the space-rocket descent in the Earth's atmosphere. Underneath the space-rocket arose the large wedge-shape after coming to each other and touching on themselves of both jalousies 88. This large wedge-shape covers the main engines underneath. Furthermore this large wedge-shape will divide and bent air stream in two directions outside the space-rocket fuselage. The large wedge-shape is the main-cover with jalousies 88 of the space-rocket main engines whereas this space-rocket will enter into the Earth's atmosphere. Here on space-rocket fuselage, the large arrows show this space-rocket descent direction in the Earth's atmosphere. Whereat the external arrows show from what direction comes flying atmospheric air and consequently in what way this air strongly crowds into both jalousies 88 which came to each other inside the U-form-rails 87. Whilst both rounded-plates 91 shield almost entirely the main engines on the both sides which are not entirely covered by main-cover with jalousies 88. Such space-rocket status will occur during the space-rocket entering in the Earth's atmosphere and its further descent until the moment whilst there will be necessary the main engines firing blast for braking action at landing. Lift upward of the sliding-engines-cover 8 can occur rapidly quickly. Here are also visible the components mentioned in descriptions of FIG. 192-195.

FIG. 212A, B, 213, 214A, B show the views of the upper and bottom parts of one booster-space-rocket 1 which descends in the first time period at giant speed in the Earth's atmosphere. Whereas FIG. 212A is the side view of the upper part, and FIG. 212B is the side view of the bottom part. And FIG. 214A is the front view of the upper part, and FIG. 214B is the side view of the bottom part. And FIG. 213 is the top view in two equal views which are rotated 90 degrees in relation to each other so that they cohere with the below views. This booster-space-rocket 1 has six spreadable-arms 5, four steering flaps 6, six blocking-bars 54 and the sliding-engines-cover 7 flat underneath. Currently all six spreadable-arms 5 are entirely lowered down and consequently are alongside the space-rocket fuselage; four flaps 6 are a little deflected out from the space-rocket fuselage for steering this space-rocket descent direction; all six blocking-bars 54 are entirely slid outside so that causing small aerodynamic braking which will stabilize this space-rocket descent; the sliding-engines-cover 7 is entirely lowered down and it causes that the space-rocket bottom is entirely covered. Such arrangement of all components and sub-assemblies of this entire booster-space-rocket 1 will occur during its descent in the first time period at giant speed in the Earth's atmosphere. On FIG. 212A, B and FIG. 214A, B, on space-rocket fuselage large arrows show the space-rocket descent direction in the Earth's atmosphere. Whereat remaining arrows show in several places what happens with the space-rocket and its sub-assemblies in such situation. These arrows show from what direction comes flying atmospheric air and consequently in what way this air strongly crowds into sliding-engines-cover 7, into six blocking-bars 54 and into four flaps 6. Simultaneously the arrows also show the deflection directions of the flaps 6 for steering the space-rocket descent direction.

And FIGS. 215A, B and 216 show the views of the upper and bottom parts of one booster-space-rocket 1 which descends in the second time period at average speed in the Earth's atmosphere. Whereas FIG. 215A is the side view of the upper part, and FIG. 215B is the side view of the bottom part. And FIG. 216 is the top view. This booster-space-rocket 1 has six spreadable-arms 5, four steering flaps 6 and the sliding-engines-cover 7 flat underneath. Currently all six spreadable-arms 5 are lifted somewhat upward and consequently protrude outside the space-rocket fuselage; four flaps 6 are a lot deflected out the space-rocket fuselage; the sliding-engines-cover 7 is entirely lowered down and it causes that the space-rocket bottom is entirely covered. Whereas all six blocking-bars 54 are entirely in the space-rocket interior because now they would not cause any aerodynamic braking. Moreover here are well visible the corner-beams 52 on space-rocket fuselage because all spreadable-arms 5 are lifted somewhat upward. Such arrangement of all components and sub-assemblies of this entire booster-space-rocket 1 will occur during its descent in the second time period at average speed in the Earth's atmosphere. This average speed of the space-rocket descent enables lift somewhat upward of all spreadable-arms 5 like on current views. On FIG. 215A, B on space-rocket fuselage, the large arrows show the space-rocket descent direction in the Earth's atmosphere. Whereat remaining arrows show in several places what happens with the space-rocket and its sub-assemblies in such situation. These arrows show from what direction comes flying atmospheric air and consequently in what way this air strongly crowds into sliding-engines-cover 7, into six spreadable-arms 5 which are lifted somewhat up, into four flaps 6 which are a lot deflected out the space-rocket fuselage. Simultaneously the arrows also show the deflection directions of the flaps 6 for steering the descent direction. During the space-rocket descent and at the same time lifting upward of each spreadable-arm 5, airflow exerts very large pressure on two lateral-beams 56 and the middle-beam 55 with the long-plate 64. The long-plate 64 permanently fastened on middle-beam 55 causes that pressure exerted on them even out with pressure exerted on two lateral-beams 56. Without the long-plate 64 pressure exerted on two lateral-beams 56 would be probably twice bigger than on one middle-beam 55 and it might too strongly push the entire spreadable-arm 5 upward.

The final arrangement status of all components and sub-assemblies of this entire space-rocket will occur during its descent in the third time period at slow speed in the Earth's atmosphere and which is shown on further FIG. 262-267. Then slow speed of the space-rocket descent in the Earth's atmosphere will enable total lift upward of all spreadable-arms 5.

FIG. 217, 218, 219, 220 show the views of one entire main-space-rocket 2 which has revolvingly installed the sectional-load-cover 4 and which is dividable into two sections by gradually folding out on two opposite sides. And the sectional-load-cover 4 is adopted to gradually folding up by pooling together both sections to total shutting. This sectional-load-cover 4 serves for covering inside some load 100 and this way creates its thermal protection during the space-rocket ascent and descent in the Earth's atmosphere. Thus inside the sectional-load-cover 4 can be fastened some load that will be carried out on Earth's orbit and later can be fastened some return-load that will be carried down on Earth. The sectional-load-cover 4 is revolvingly installed on main-space-rocket 2 upper part and can be situated above the second-stage-rocket 3. The sectional-load-cover 4 can be completely lowered down to main-space-rocket 2 upper part as well. This sectional-load-cover 4 is attached to main-space-rocket 2 by means of four long cog-beams 93. Currently to main-space-rocket 2 is also directly attached the second-stage-rocket 3. Here the sectional-load-cover 4 is shut up and all cog-beams 93 are outside and on both sides of the second-stage-rocket 3. Whilst, inside the sectional-load-cover 4 is placed the load 100 which will be carried out on Earth's orbit. This load 100 is attached to second-stage-rocket 3. Whereas FIG. 217 shows the side view of one entire main-space-rocket 2 which is ready for launch. And FIG. 218 shows the front view of the same main-space-rocket 2. Whereat FIG. 219 is the same like FIG. 217 albeit contains the load 100 sketches inside the shut up sectional-load-cover 4 and the second-stage-rocket 3 sub-assemblies sketches which are veiled by some other modules. Whereat FIG. 220 is the same like FIG. 218 albeit contains the same sketches like FIG. 220. Moreover on FIGS. 217 and 219 the external arrows show the spreading directions of the sectional-load-cover 4 into two sections on two sides.

FIG. 221 is the side view of the second-stage-rocket 3 whereon is attached the load 100 which will be carried out on Earth's orbit. Here the second-stage-rocket 3 has one nozzle 85 which is foldable.

FIG. 222 is the side view of the second-stage-rocket 3 where-from ascends the load 100.

FIG. 223, 224 show the enlarged views of the main-space-rocket 2 upper part which were earlier shown on FIG. 219-220. Here the main-space-rocket 2 upper part has revolvingly installed the sectional-load-cover 4 which is dividable into two sections and gradually foldable out on two opposite sides. And later this sectional-load-cover can be gradually pooled together up to total shutting. This sectional-load-cover 4 is revolvingly installed to main-space-rocket 2 by means of four cog-beams 93. Now to main-space-rocket 2 is also directly attached the second-stage-rocket 3. Here the sectional-load-cover 4 is shut up and all cog-beams 93 are outside and on both sides of the second-stage-rocket 3. Whilst, inside the sectional-load-cover 4 is placed the load 100 that will be carried out on Earth's orbit. This load 100 is attached to second-stage-rocket 3. And FIG. 223 shows the side view of the main-space-rocket 2 upper part and contains the load 100 sketches inside the shut up sectional-load-cover 4 and contains the second-stage-rocket 3 fragments sketches which are veiled by other modules. Here the external arrows also show the spreading directions of the sectional-load-cover 4 into two sections on two sides. This view shows that the sectional-load-cover 4 can divide into two sections and can fold out on two opposite sides, because it is two-sectional and is installed to main-space-rocket 2 by means of four cog-beams 93. And FIG. 224 shows the front view of the main-space-rocket 2 upper part and contains the same fragments like FIG. 223. Here is visible that to main-space-rocket 2 upper part are installed four rotating-heads 94 of the cog-beams 93. These rotating-heads 94 are in this space-rocket interior and are in two opposite sides of this space-rocket fuselage. Each rotating-head 94 is driven by one servomotor with one reduction gear which rotate the rotating-axle 95. The rotating-axles 95 of the rotating-heads 94 are permanently fastened to cog-beams 93 which are outside the space-rocket fuselage. Therefor all four cog-beams 93 can incline on sides and with them also both sections of the sectional-load-cover 4. Each one section of the sectional-load-cover 4 is held up and incline by two cog-beams 93. The cog-beams 93 are long and are outside on both sides of the second-stage-rocket 3. All cog-beams 93 come up and enter inwards both sections of the sectional-load-cover 4. Whilst inside the sectional-load-cover 4 each cog-beam 93 is held up by means of one hoisting-gear 96. Each one section of this sectional-load-cover 4 has installed its own two hoisting-gears 96, namely of lifting up itself. Each hoisting-gear 96 is driven by one servomotor with one reduction gear which rotates one cog-wheel 97 which is fitted with one cog-beam 93. All cog-beams 93 protrude suitably up above the hoisting-gears 96 so that it would be possible to initially lift up the entire sectional-load-cover 4. The cog-beams 93 protruding up inside the sectional-load-cover 4 are visible on current views and are indicated with the large exclamatory sign.

FIG. 225, 226 show the enlarged views of the main-space-rocket 2 upper part shown also earlier on similar FIG. 223-224. Currently the sectional-load-cover 4 is lifted maximally upward on four long cog-beams 93. This enables spreading it out on two sides. On current FIG. 225, the external arrows show spreading directions of the sectional-load-cover 4 into two sections on two sides. Whereas FIG. 225 is the side view, FIG. 226 is the front view. Here is visible vacant space between the sectional-load-cover 4 bottom edge and the second-stage-rocket 3 upper edge. This vacant space is visible on current views and is indicated with the large exclamatory sign. In this vacant space is already directly visible the fragment of the load 100 that will be carried out on Earth's orbit. The sectional-load-cover 4 became lifted maximally upward on four cog-beams 93 because rotating four cog-wheel 97 climbed up on four cog-beams 93. The four cog-wheel 97 are driven by four hoisting-gears 96.

FIG. 227 shows enlarged side view of the main-space-rocket 2 upper part shown earlier on FIG. 223-225. Here the sectional-load-cover 4 is already spread a little out on two sides. It is possible because there is vacant space between the sectional-load-cover 4 bottom edge and the second-stage-rocket 3 upper edge. This vacant space is visible on current view and is indicated with two large exclamation marks. This view well shows, in what way the sectional-load-cover 4 can be folded out on two sides because it is two-sectional and is installed to main-space-rocket 2 by means of four cog-beams 93. Simultaneously it is visible that the cog-beams 93 are rotatably installed to main-space-rocket 2 frame. These cog-beams 93 are permanently fastened to rotating-axles 95 which are rotated by rotating-heads 94. All rotating-axles 95 became rotated tiny angle and it rotated the same tiny angle all entire cog-beams 93 and with them also both sections of sectional-load-cover 4. Here the entire cog-beams 93 are continuously outside and on both sides of second-stage-rocket 3. Currently is already a lot uncovered the load 100 which will be carried out on Earth's orbit.

FIG. 228 shows very diminished the side view of one entire main-space-rocket 2 that has entirely folded out on two sides the sectional-load-cover 4 and shows the sketch its intermediate folding out. Because of total folding out on two sides the sectional-load-cover 4 there is entirely uncovered the load 100 which is attached to second-stage-rocket 3.

FIG. 229 shows the side view of the main-space-rocket 2 upper part which has entirely folded out on two sides the sectional-load-cover 4 and the sketch its intermediate folding out. Because of total folding out on two sides the sectional-load-cover 4, there is entirely uncovered the load 100 which is attached to second-stage-rocket 3. Whilst this second-stage-rocket 3 is still attached to main-space-rocket 2.

FIG. 230 shows the side view of the main-space-rocket 2 upper part which has also entirely folded out the sectional-load-cover 4. And here the second-stage-rocket 3 with attached load 100 ascend together upward because they already separated from the main-space-rocket 2. All earlier views well show in what way the sectional-load-cover 4 can be folded out on two sides because it is two-sectional and is installed to main-space-rocket 2 by means of four cog-beams 93. Simultaneously it is visible that the cog-beams 93 are rotatably installed to main-space-rocket 2 frame.

FIG. 231 shows the side view of the main-space-rocket 2 upper part which has entirely folded out on two sides the sectional-load-cover 4. Here the second-stage-rocket 3 with attached return-load 106 approach together to main-space-rocket 2 in order to dock with it. The second-stage-rocket 3 has the nozzle 85 which is folded for more safely docking.

FIG. 232 shows the side view of the main-space-rocket 2 upper part whereto is already docked the second-stage-rocket 3 with attached return-load 106. Here the sectional-load-cover 4 is already a little shut up. Sequentially the sectional-load-cover 4 will be shut totally up and consequently will hide inside the entire return-load 106 from the Earth's orbit.

FIG. 233, 234, 235, 236 show the views of the alone main-space-rocket 2 upper part ergo without docked the second-stage-rocket 3. Whereas FIG. 233 shows the side view of the alone main-space-rocket 2 upper part which has entirely folded out on two sides the sectional-load-cover 4. And FIG. 234 shows the top view of the alone main-space-rocket 2 upper part which has entirely folded out on two sides the sectional-load-cover 4. And FIG. 233-234 well show in what way the sectional-load-cover 4 can be folded out on two sides because it is two-sectional and is installed to main-space-rocket 2 by means of four cog-beams 93. Simultaneously it is visible that the cog-beams 93 are rotatably installed to main-space-rocket 2 frame. And here is clearly visible emplacement of four uncovered hoisting-gears 96 of the sectional-load-cover 4 both sections. Moreover it is clearly visible emplacement of four uncovered rotating-heads 94 of the cog-beams 93. And FIG. 235 shows the side view of the main-space-rocket 2 upper part which has a little shut up the sectional-load-cover 4. And FIG. 236 shows the side view of the main-space-rocket 2 upper part which has even more shut up the sectional-load-cover 4.

FIG. 237-243 show the views of the alone main-space-rocket 2 upper part ergo without docked the second-stage-rocket 3. Whereas FIG. 237 shows the side view of the main-space-rocket 2 upper part which is very near to shutting up the sectional-load-cover 4. This view and the earlier views from FIG. 232 well show in what way both sections of the sectional-load-cover 4 can be gradually pooled together up to total shutting. And FIG. 238, 239 show the side view and the front view of the main-space-rocket 2 upper part which has the sectional-load-cover 4 entirely shut up. This sectional-load-cover 4 is maximally distant upward from the main-space-rocket 2 and it is held up by means of four long cog-beams 93. The entire cog-beams 93 are by themselves above the main-space-rocket 2 and are under the sectional-load-cover 4. Here the arrows under the sectional-load-cover 4 show the direction its lowering down to main-space-rocket 2. This entire sectional-load-cover 4 will be lowered further down on four cog-beams 93. And FIG. 240, 241 show the side view and the front view of the main-space-rocket 2 upper part which has also the entirely shut up sectional-load-cover 4. This sectional-load-cover 4 is already lowered a lot down on four cog-beams 93. After lowering down the sectional-load-cover 4, four cog-beams 93 upper ends entered a lot inwards this sectional-load-cover 4. Here the arrows under the sectional-load-cover 4 show the direction its further lowering down to main-space-rocket 2. And FIG. 242, 243 show the side view and the front view of the main-space-rocket 2 upper part which has also the entirely shut up sectional-load-cover 4. This sectional-load-cover 4 is already entirely lowered down on four cog-beams 93. Consequently this sectional-load-cover 4 touched on with the main-space-rocket 2 frame. Therewith four entire cog-beams 93 entered entirely inwards this sectional-load-cover 4. Lowering down of the sectional-load-cover 4 targets its fastening with the main-space-rocket 2 frame which is necessary for landing without the second-stage-rocket 3.

FIG. 244, 245, 246, 247 show the enlarged views of the totally shut up sectional-load-cover 4 which is revolvingly installed to main-space-rocket 2 upper part. This sectional-load-cover 4 was earlier lowered down on four cog-beams 93 to main-space-rocket 2 frame like it were shown on previous FIGs. Therewith four entire cog-beams 93 entered entirely inwards the sectional-load-cover 4. For this reason these entire cog-beams 93 are sketched with the dashed lines. Here is visible in what way are installed four hoisting-gears 96 of the sectional-load-cover 4 and four rotating-heads 94 of four cog-beams 93. And FIG. 244 is the side view. And FIG. 245 is the top view of the horizontal sectional view according to S1-S1 line on FIG. 244. Here are visible only components inside the sectional-load-cover 4 thus its four hoisting-gears 96. Each one hoisting-gear 96 is driven by one servomotor with one reduction gear which rotates the cog-wheel 97 which is fitted with some cogs in the cog-beams 93. All cog-beams 93 have plenty internal cogs in their internal insides. All cog-beams 93 are rectangular in cut-view and are placed slidingly inside some rectangular-tubes 99. These rectangular-tubes 99 are permanently fastened to both bottoms of the sectional-load-cover 4. All cog-beams 93 and all rectangular-tubes 99 must be rectangular in cut-view so that there would not occur angular contorsion of any section of the sectional-load-cover 4. And FIG. 246 is the top view of the horizontal sectional view according to S2-S2 line on FIG. 247. Here are visible only components inside the main-space-rocket 2 thus four rotating-heads 94 of the cog-beams 93 whereby incline the sectional-load-cover 4. These rotating-heads 94 are in the space-rocket interior and are on two opposite sides of this space-rocket fuselage. Each one rotating-head 94 is driven by one servomotor with one reduction gear which rotates the rotating-axles 95. The rotating-axles 95 are permanently fastened to cog-beams 93 which are outside the space-rocket fuselage. Therefor all four cog-beams 93 can incline on sides and with them also both sections of this sectional-load-cover 4. And FIG. 247 is the front view of FIG. 244 in the same arrangement and situation.

FIG. 248, 249 show the enlarged views of the fragments of the entirely shut up sectional-load-cover 4 and of the main-space-rocket 2 upper part. Whereas FIG. 248 is the side view. And FIG. 249 is the front view. Here the sectional-load-cover 4 is a little lifted upward on four cog-beams 93 and therefor a little protrude from the main-space-rocket 2. For this reason all four cog-beams 93 upper ends are situated inside the sectional-load-cover 4. And inside the sectional-load-cover 4 are visible its four hoisting-gears 96. Furthermore, inside the main-space-rocket 2 are visible four rotating-heads 94 of the cog-beams 93.

FIG. 250, 251, 252 show very plenty enlarged and detailed views of two hoisting-gears 96 in the fragments of the entirely shut up sectional-load-cover 4 which is lifted up. And FIG. 250 is the side view, FIG. 251 is the top view, FIG. 252 is the front view. Here is well visible installation way and construction of one entire hoisting-gear 96 which is driven by a servomotor with one reduction gear which rotates the cog-wheel 97 and which is fitted with the cog-beam 93. All cog-beams 93 have plenty internal cogs in their internal insides. All cog-beams 93 are rectangular in cut-view and are placed slidingly inside rectangular-tubes 99. There are two rectangular-tubes 99 permanently fastened to each one section bottom of the sectional-load-cover 4. Hence together there are four rectangular-tubes 99 because there are four cog-beams 93.

FIG. 253, 254, 255 show very plenty enlarged and detailed views of two rotating-heads 94 of the cog-beams 93 in the fragments of the main-space-rocket 2 frame. And FIG. 253 is the side view, FIG. 254 is the top view, FIG. 255 is the front view. Here is visible installation way and construction of these entire rotating-heads 94 of the cog-beams 93. These rotating-heads 94 are installed to thick-plates 98 which are permanently fastened to frame upper part of this main-space-rocket 2. Each rotating-head 94 is driven by one servomotor with one reduction gear which rotates the rotating-axle 95. The rotating-axles 95 are situated in the holes in the thick-plates 98. The rotating-axles 95 are permanently fastened to cog-beams 93 which are outside the space-rocket fuselage. Therefor all four cog-beams 93 will incline whilst the rotating-axles 95 will somewhat rotate. And together with the cog-beams 93 will incline also suitable sections of this sectional-load-cover 4. Here the arrows show the moving directions of some components.

FIG. 256, 257, 258, 259 show the views of the entire main-space-rocket 2 which is attached in two variants with a load-module 103 and a crew-module 102 and which were not shown on any earlier views. The load-module 103 has two gates with a cargo bay whilst the crew-module 102 has some windows. Here the main-space-rocket 2 is also equipped with ten spreadable-arms 5 so that this space-rocket with current assemblage could land aboard the ship 10 with deck-mounted landing-station. Whereas FIG. 256-257 show the attaching variant wherein on main-space-rocket 2 top is mounted the assemblage which consist of the second-stage-rocket 3 whereon is attached the load-module 103 and whereto is attached the crew-module 102. Whereat FIG. 256 is the side view, FIG. 257 is the front view. This attaching variant will be applied whilst on Earth's low orbit this assemblage will separate from the main-space-rocket 2. Separating purpose can be that this assemblage will scheduled ascend toward the Earth's high orbit. Later this entire separated assemblage will be able to come back and dock to the same main-space-rocket 2 so that afterward together return on Earth. Whereas FIG. 258-259 show the attaching variant wherein on main-space-rocket 2 top is mounted the assemblage which only consists of the load-module 103 with attached crew-module 102. And FIG. 258 is the side view, FIG. 259 is the front view. Such attaching variant will be applied whilst on Earth's orbit this assemblage will not separate from the main-space-rocket 2. Thus here is not the second-stage-rocket 3.

FIG. 260 is the side view of the separated assemblage which consist of the second-stage-rocket 3 with attached load-module 103 whereto is attached the crew-module 102. It is the same assemblage that is attached to main-space-rocket 2 on FIG. 256-257.

FIG. 261 is the side view of the alone crew-module 102 which in such status would be used only for emergency separation from the assemblage and thus from the space-rocket.

Purposes of the views on FIG. 256-261 are presentations that the main-space-rocket 2 equipped with ten spreadable-arms 5 can have mounted on its top some various assemblages or modules and together with them can also land aboard the ship 10 that has deck-mounted landing-station. Shown here the attaching variants of the main-space-rocket 2 with the load-module 103 and with the crew-module 102 enable the same possibilities of utilization like had earlier applied Space Shuttles.

FIG. 262-267 show examples of descending in the Earth's atmosphere of one booster-space-rocket 1 and of the main-space-rocket 2 with on its top mounted various assemblages and in various variants. These space-rockets descend in the Earth's atmosphere during the third so the last time period at slow speeds and therefor all space-rockets could already entirely lift upward their all spreadable-arms 5 and entirely deflected out their all steering flaps 6. All space-rockets still have totally shut down their sliding-engines-cover 7. On all space-rocket-frames the large arrows show their descent direction in the atmosphere. Whereat the external arrows show from what direction come flying atmospheric air. Therefore these arrows show in what way the air strongly crowds into all sub-assemblies, sections, assemblages and modules of these space-rockets. Whereas FIG. 262-263 show the side view and the top view of one booster-space-rocket 1 which has entirely lifted up (spread out) its all six spreadable-arms 5. This booster-space-rocket 1 has not any attached module. Whereas FIG. 264-265 show the side view and the top view of one main-space-rocket 2 which has entirely lifted upward (spread out) its all ten spreadable-arms 5. This main-space-rocket 2 has on its top directly attached the sectional-load-cover 4. This attaching and landing variant of the main-space-rocket 2 could be whilst the second-stage-rocket 3 will remain on Earth's orbit. This attaching and landing variant can also occur if the sectional-load-cover 4 is installed in different way, for example by some hinges to main-space-rocket 2. Whereas FIG. 266 shows the side view of one main-space-rocket 2 which has also entirely lifted up (spread out) all ten spreadable-arms 5. Here is the attaching variant wherein on main-space-rocket 2 top is mounted the assemblage that consist of the second-stage-rocket 3 with the sectional-load-cover 4. Here is visible that all cog-beams 93 are outside and on both sides of the second-stage-rocket 3. This attaching and landing variant of the main-space-rocket 2 will be whilst the second-stage-rocket 3 will be taken back from the Earth's orbit. And this attaching variant causes that inside the sectional-load-cover 4 can be some load taken back from the Earth's orbit. For example, a large satellite taken back for repair. Whereas FIG. 267 shows the side view of one main-space-rocket 2 which has also entirely lifted up (spread out) all ten spreadable-arms 5. The view shows the attaching variant wherein on main-space-rocket 2 top is mounted the assemblage that consist of the second-stage-rocket 3 with attached load-module 103 and the crew-module 102. This attaching variant of the main-space-rocket 2 will be whilst the second-stage-rocket 3 will be taken back from the Earth's orbit with attached load-module 103 and the crew-module 102. This attaching variant causes that inside the load-module 103 can be some load taken back from the orbit.

FIG. 268, 269 show the front views of one main-space-rocket 2 which is joined on both sides with two booster-space-rockets 1. And FIG. 268 is the diminished front view of three joined space-rockets. And FIG. 269 is the enlarged front view of the upper parts of the same three joined space-rockets which are on FIG. 268. On main-space-rocket 2 top is mounted the assemblage which consist of the second-stage-rocket 3 with sectional-load-cover 4. Whereat the sectional-load-cover 4 is directly attached to second-stage-rocket 3 and is revolvingly installed to main-space-rocket 2 by means of the cog-beams 93. And inside the sectional-load-cover 4 is fastened some load which will be carried out on Earth's orbit. In such status and arrangement these three joined space-rockets are entirely ready for launch toward space. These views target presentation that the spreadable-arms 5 fastened to main-space-rocket 2 and to two booster-space-rockets 1 do not hinder joining them with themselves. These three space-rockets are joined with themselves by means of some foldable crossbars without any numbers.

FIG. 270 shows the enlarged side view of the entire ship 10 which has deck-mounted landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. And alongside is just such space-rocket. This view is the same like FIG. 11 albeit is enlarged. On current view are best visible two edge-bars 50 which are permanently fastened on two long side-hulls 11. Both these edge-bars 50 lead all wheels 16 of both movable-decks 15 whilst they roll on main-deck 14. Accurate description of this view is the same like previous FIG. 11 and therefor is not quoted here.

FIG. 271 shows the enlarged top view of the entire ship 10 which has deck-mounted landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. And alongside is just such space-rocket. This view is the same like FIG. 12 albeit is enlarged. On current view are best visible two edge-bars 50 which are permanently fastened on two long side-hulls 11. Both these edge-bars 50 lead all wheels 16 of both movable-decks 15 whilst they roll on main-deck 14. Accurate description of this view is the same like previous FIG. 12 and therefor is not quoted here.

FIG. 272 shows the enlarged front view of the entire ship 10 which has deck-mounted landing-station for individual, vertical landing and also for fastening of three space-rockets equipped with several spreadable-arms 5. And alongside is just such space-rocket. This view is the same like FIG. 13 albeit is enlarged. On current view are best visible two edge-bars 50 which are permanently fastened on two long side-hulls 11. Both these edge-bars 50 lead all wheels 16 of both movable-decks 15 whilst they roll on main-deck 14. Accurate description of this view is the same like previous FIG. 13 and therefor is not quoted here.

FIG. 273 is prospectus presentation which shows for example several drawing statuses of one main-space-rocket 2 which lifted-off and its further traveling trajectory whilst unexpectedly happened failure of some main engine. The current presentation shows process of this entire main-space-rocket 2 salvation and its emergency landing aboard the ship 10 at open sea. On this space-rocket drawing statuses and alongside the arrows show the directions of its traveling trajectory. As result of such method, in some circumstances there is possible total salvage of the main-space-rocket 2 together with entire assemblage. And this view display also that each space-rocket equipped with spreadable-arms 5 can in some other emergency land aboard the ship 10.

The views on FIG. 274, 275 show for example one booster-space-rocket 1 which slips by through the wide-opened interior of the ship 10 at open sea. And FIG. 274 is the side view, FIG. 275 is the top view. According to plan, this booster-space-rocket 1 was supposed to land on this ship 10. However during this space-rocket descent happened some failure of the main engines which were supposed to bring total stop of the space-rocket descent and make possible landing aboard the ship 10. In order to prevent any strike of this space-rocket onto ship 10 there were quick and entirely spread apart in two directions both movable-decks 15. Both deck-gantries 20 were already earlier entirely spread apart in two directions of the ship 10. As result, inside the ship 10 hull arose the jumbo abyss wherein there is only sea-water. Accurately into this abyss filled with sea-water struck hard this booster-space-rocket 1 and plunged in sea-water. Therefore, this booster-space-rocket 1 did not strike into any member of the ship 10. This space-rocket became lost but the entire ship 10 survived and that is giant economic profit. Moreover this ship 10 and the landing-station are immediately ready for landing the next space-rocket, because there will only be enough to push together both movable-decks 15. On views are distinctly visible water splashes which arose after the space-rocket stroke onto sea surface.

INFORMATION about the present invention. While the present invention has been described in terms of particular embodiments and applications, in both summarized and detailed forms, it is not intended that these descriptions in any way limit its scope to any such embodiments and applications, and it will be understood that many substitutions, changes and variations in the described embodiments, applications and details of the method and system illustrated herein and of their operation can be made by those skilled in the art without departing from the spirit of this invention.

REFERENCE NUMBERS

Main Numbers.

-   1 booster-space-rocket, 2 main-space-rocket, 3 second-stage-rocket,     4 sectional-load-cover (dividable into two sections), 5     spreadable-arm (six or ten), 6 flap (four), 7 sliding-engines-cover     flat underneath (one), 8 sliding-engines-cover wedge-shaped     underneath (one), 9 exhaust-fume (gushing from space-rocket main     engines), 10 ship. -   Sub-assemblies of the ship 10. -   11 long side-hull (two), 12 short central-hull (two), 13     copular-hull (four), 14 main-board, 15 movable-deck (two), 16 wheel     (many of both movable-decks 15), 17 tunnel (two inside the ship 10     hull), 18 ballasting-wagon (two in tunnels 17), 19 main-rail (two     for rolling of both deck-gantries 20). -   Sub-assemblies of the deck-gantries 20. -   20 deck-gantry (two), 21 wheel (many), 22 bumper (two), 23     upper-long-rail (two on each deck-gantry 20). -   Sub-assemblies of the hangers 24. -   24 hanger (four), and in each hanger—25 rotating-wedge (two), 26     upper-short-rail (two), 27 rotary-actuator (two), 28 support-axle     (one), 29 rotating-axle (one for each rotary-actuator 27). -   Sub-assemblies of the damping-wagons 30 and 31. -   30 damping-wagon (four), 31 large damping-wagon (two), 32     flexible-layer, 33 wedge-shaped-fender, 34 leading-shafts, 35     main-plate, 36 high-leading-tube, 37 low-leading-tube, 38     middle-plate, 39 conic-spring, 40 top-plate, 41 driving-wheel, 42     leading-wheel, 43 battery. -   Sub-assemblies of the grasping-wagons 44. -   44 grasping-wagon (two), 45 rotating-poles (two in each     grasping-wagon 44), 46 wheel (many). -   Sub-assemblies of the ship 10. -   47 long-transverse-rail (two on each movable-deck 15), 48     short-transverse-rail (four on pillars 49), 49 pillar (many on     main-boards 14), 50 edge-bar (two fastened on both long side-hulls     11). -   Sub-assemblies of the space-rockets. -   51 space-rocket-tube (one fragment), 52 corner-beam (many on     space-rocket fuselage). -   Sub-assemblies of the spreadable-arms 5 and in each. -   53 slider (one), 54 blocking-bar (one), 55 middle-beam (one), 56     lateral-beam (two). -   Sub-assemblies of the steering flaps 6 and their deflection     mechanisms. -   57 ample-bracket, 58 rotary-actuator, 59 torsional-triangle, 60     linear-actuator. -   Sub-assemblies of the space-rockets. -   61 pressure-tank, 62 limiter. -   Sub-assemblies of the spreadable-arms 5. -   63 bearing-axle, 64 long-plate, 65 common-long-axle, 66     holding-axle, 67 T-bar, 68 frictional-brake. -   Sub-assemblies of the pushing mechanisms of blocking-bars 54. -   69 large-C-profile, 70 linear-actuator, 71 vertical-low-bar. -   Sub-assemblies of the spreadable-arms 5 and their moving mechanisms. -   72 flat-bar (has oval-opening), 73 servomotor, 74 worm-gear, 75     threaded-pipe, 76 special-nut, 77 cylindrical-peg, 78 common-roller,     79 bearing-seat, 80 bearing-bracket (with the hole), 81     distance-block. -   Sub-assemblies of the frictional-brakes 68. -   82 brake-block, 83 linear-actuator, 84 ending-bracket (with the     hole). -   Sub-assemblies of the space-rockets. -   85 nozzle (of the space-rocket main engine). -   Sub-assemblies of the sliding-engines-covers 7 and 8. -   86 flat carrying-plate (four), 87 long U-form-rail (two), 88     jalousie (two), 89 side-plate (two), 90 angle-profile (four), 91     rounded-plate (two), 92 stiffening-beam (two). -   Sub-assemblies of the sectional-load-cover 4. -   93 cog-beam (four), 94 rotating-head (four), 95 rotating-axle     (four), 96 hoisting-gear (four), 97 cog-wheel (four), 98 thick-plate     (two), 99 rectangular-tube (four in the sectional-load-cover 4). -   Other Numbers. -   100 load (will be carried on Earth's orbit), 101 Earth's globe, 102     crew-module, 103 load-module, 104 ground-gantry (two movable), 105     ground-crane (one movable), 106 return-load (from the Earth's     orbit). 

1. A utter system for multiple use of space-rockets equipped with spreadable-arms and possibly more devices, and method of these space-rockets vertical landing by hanging on landing-station having gantries and more apparatus comprising: the space-rockets equipped with the spreadable-arms which are adopted for vertical landing by hanging on gantries; and the space-rockets can comprise some steering flaps, a dividable sectional-load-covers, a sliding-engines-covers having jalousies; and wherein the utter system comprises the landing-station having the movable gantries and can comprise the hangers and the grasping-wagons, and wherein the hangers can comprise rotating-wedges, and wherein the gantries can comprise some damping-wagons and which all are adopted for vertical landing of the space-rockets, and wherein the landing-station is adopted to be on land or can be deck-mounted on ship, and the ship can comprise some joined hulls, horizontally movable-decks and ballasting-wagons and which all are adopted for vertical landing of the space-rockets; and the utter system can comprise a harbor terminal adapted for the space-rockets reload, launch, landing and which harbor terminal comprises two movable ground-gantries and can comprise a ground-crane, and wherein the harbor terminal is adapted to be the landing-station as well.
 2. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claim 1, wherein each space-rocket comprises: at least two spreadable-arms suitably spaced out in the space-rocket fuselage so that they could spread out on two sides, wherein all spreadable-arms are adopted to being entirely lowered down alongside the space-rocket fuselage during its ascent, and are adopted to be lifted partly or entirely upwards hence spread out for usage as the aerodynamic brake during the space-rocket descent, and are adopted to be lifted entirely upwards hence completely spread out and being transverse the space-rocket fuselage for hanging up the space-rocket on gantries during landing.
 3. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claims 1 and 2, wherein each spreadable-arm comprises: at least two lateral-beams, a middle-beam, a moving mechanism installed inside the space-rocket fuselage, a slider movable between two corner-beams fastened on space-rocket fuselage, wherein both lateral-beams tops are bent and are inside the space-rocket fuselage, and wherein both lateral-beams upper bent parts can comprise permanently fastened some flat-bars having oval-openings adopted to a servomotor, and wherein both lateral-beams tops are rotatably joined with the space-rocket fuselage by means of two bearing-axles which are situated in four bearing-brackets, and wherein the middle-beam top is rotatably joined with the bottoms of both lateral-beams, and wherein the middle-beam bottom is rotatably joined with a slider, and wherein inside the middle-beam bottom is installed a frictional-brake, and wherein on middle-beam can be permanently fastened a bar adopted to fit with a groove in the blocking-bar, and wherein each spreadable-arm moving mechanism comprises some servomotor which is adopted for moving both lateral-beams top bent parts;
 4. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claims 1, 2 and 3 wherein each space-rocket can comprise: a pushing mechanism mounted inside the space-rocket fuselage and above the spreadable-arm, and wherein the pushing mechanism comprises a blocking-bar which is adopted for blocking the middle-beam in all directions whilst the spreadable-arm is entirely lifted up, and wherein the blocking-bar fulfills blocking purpose when is maximally slid outside, and wherein the pushing mechanism comprises a large-C-profile, a linear-actuator, a vertical-low-bar and the blocking-bar, and wherein the pushing mechanism is adopted for pushing and pooling the blocking-bar, and wherein each blocking-bar comprises a groove which is adopted to fit with the a bar permanently fastened on middle-beam in the spreadable-arm.
 5. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claim 1, wherein the space-rocket can comprise: some steering flaps cardinally installed on space-rocket upper part and which are adopted to steer the space-rocket during its descent in atmosphere, wherein each flap is cardinally installed by means of hinges to the space-rocket fuselage, and wherein each flap is deflected by some deflection mechanism having a linear-actuator and two ample-brackets, and wherein steering flaps can comprise some rotary installed torsional-triangles which are adopted for precise steering of entire space-rocket axial torsion, needed before landing on two deck-gantries, and wherein the torsional-triangles are triangular so that they could be used at all speeds and stages of the space-rocket descent in the atmosphere, and wherein each torsional-triangle comprises rotary-actuator adopted for axial torsion of the torsional-triangles, and wherein each rotary-actuator strongly grasps and steers axial torsion of the torsional-triangles.
 6. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claim 1, wherein the space-rocket can comprise: the dividable sectional-load-cover which is adopted to dividing in two sections by gradually folding out, and is adopted to gradually folding up by pooling together to total shutting, and is adopted for covering inside some load and this way creating its thermal protection during the space-rocket ascent and descent in the atmosphere, and is adopted to be revolvingly installed on space-rocket upper part and being situated above the second-stage-rocket, wherein entire sectional-load-cover is revolvingly installed to the space-rocket by means of four cog-beams, and wherein each one section of the sectional-load-cover is held up and incline by two cog-beams, and wherein all cog-beams are situated outside and on two opposite sides of the space-rocket and this way also outside and on two opposite sides of the second-stage-rocket if it is applied, and wherein each cog-beam is revolvingly installed to the space-rocket fuselage by means of a rotating-head, and wherein each rotating-head is mounted inside the space-rocket, and wherein each rotating-head comprise a rotating-axle to which is permanently fastened one cog-beam, and wherein each rotating-head is driven by one servomotor with one reduction gear which rotate the rotating-axle; and the dividable sectional-load-cover is adopted to be lifted somewhat above the second-stage-rocket before folding out on two opposite sides, and is adopted to be completely lowered down to the space-rocket upper part when the second-stage-rocket is not used, and wherein each one section of the sectional-load-cover has installed its own two hoisting-gears for lifting up itself, and wherein each hoisting-gear is mounted inside the sectional-load-cover, and wherein inside the sectional-load-cover each cog-beam is held up by means of one hoisting-gear, and wherein all cog-beams protrude suitably up above the hoisting-gears inside the sectional-load-cover so that it would be possible to initially lift up the entire sectional-load-cover, and wherein each hoisting-gear is driven by one servomotor with one reduction gear which rotates one cog-wheel which is fitted with one cog-beam.
 7. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claim 1, wherein the space-rocket can comprise: the sliding-engines-cover which comprises the main-cover having two sliding jalousies and can comprise two sliding rounded-plates; and wherein each entire sliding-engines-cover is adopted to be rapidly shut down (by sliding down) or rapidly opened (by sliding up), and wherein the sliding-engines-cover is adopted to cover the space-rocket main engines during atmospheric reentry and this way creates their thermal protection, and is adopted to be lifted entirely upward during running the space-rocket main engines ergo during the space-rocket liftoff and during braking action at space-rocket landing; and wherein the main-cover having two sliding jalousies can be adopted to be flat underneath or wedge-shaped underneath after their lowering down, and wherein the main-cover with jalousies is installed to the space-rocket fuselage bottom by means of four flat carrying-plates, and wherein each main-cover comprises two long U-form-rails, two stiffening-beams, two sliding jalousies wherewith each is joined by hinges with one side-plate, and wherein all flat carrying-plates are permanently fastened to the space-rocket fuselage, and wherein to all flat carrying-plates are permanently fastened two long U-form-rails, and wherein both U-form-rails stretch on from the space-rocket fuselage one side to its bottom and further to the space-rocket fuselage opposite side, and wherein the opposite U-form-rails upper ends are permanently fastened with themselves and with the space-rocket fuselage by means of two stiffening-beams, and wherein in both U-form-rails are placed two jalousies wherewith each one is joined by hinges with one side-plate, and wherein both jalousies with the side-plates are placed on two opposite sides of the space-rocket fuselage, and wherein both jalousies with the side-plates are adopted to move slidingly in two U-form-rails, and wherein both jalousies are adopted to come to each other and touch on themselves in the U-form-rails bottom and in their middle, and wherein after lowering down of both jalousies underneath the space-rocket arises a square flat surface or wedge-shaped surface which covers the main engines underneath; and wherein the sliding-engines-cover can comprise two sliding rounded-plates, and wherein both sliding rounded-plates after their lowering down are adopted to shield almost entirely the main engines on the both sides which are not entirely covered by main-cover with jalousies, and wherein both sliding rounded-plates are situated on two opposite sides of the space-rocket fuselage, and wherein each rounded-plate can move slidingly down and up in two angle-profiles, and wherein all four angle-profiles are permanently fastened to the space-rocket fuselage.
 8. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claim 1, wherein the landing-station comprising: two movable gantries and can comprise a few hangers, a few grasping-wagons and which all are adopted for vertical landing of the space-rockets equipped with spreadable-arms; wherein the landing-station is adopted to be on land having two movable ground-gantries, and wherein the landing-station is adopted to be deck-mounted on ship having two movable deck-gantries and can comprise a few hangers and a few grasping-wagons, and wherein one par of the hangers are adopted to be installed on each side of the gantries. and wherein the grasping-wagons are adopted to be installed underneath the gantries.
 9. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claims 1 and 8: wherein all moving gantries can comprise a few rails fixed on their tops and which are adopted for several damping-wagons, and wherein all movable gantries can comprise that on their tops are placed several damping-wagons, and wherein two movable gantries are adopted to approach to each over before landing of the space-rocket, and wherein two movable gantries are adopted to place themselves precisely under landing space-rocket equipped with spreadable-arms, and wherein both movable deck-gantries comprise some wheels to precisely move on deck-rails along the ship length, and wherein both movable ground-gantries comprise some wheels to precisely move about on ground and turn on it. and wherein two gantries can approach to each over and touch on themselves with the bumpers,
 10. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claims 1, 8 and 9 wherein the hangers can comprise: a few rails fixed on their tops which are adopted for several damping-wagons, and can comprise the rotating-wedges; wherein on each hanger top are fix a few rails whereon can roll in one damping-wagon, and wherein the rails on hangers tops are fitted with the rails on movable gantries tops, and wherein the space-rocket equipped with spreadable-arms hanged on two damping-wagon can be quick moved from two gantries to one par of the hangers, and wherein one par of the hangers can be on each side of the gantries, and wherein one par of the hangers is adopted for hanging one space-rocket equipped with spreadable-arms and fastening it at bottom by means of four rotating-wedges, and wherein the hangers are permanently fastened onto main deck of the ship and thus are immobile, and wherein each hanger can comprise two rotating-wedges which are adopted for blocking and fastenings of one space-rocket equipped with spreadable-arms, and wherein the opposite hangers have the rotating-wedges mounted on varied heights so that they would not hook each over, and wherein two rotating-wedges which are installed on one hanger have a common support-axle, and wherein each rotating-wedge has its own rotating-axle and rotary-actuator adopted to be rotated apart other rotating-wedges.
 11. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claims 1, 8, 9 and 10, wherein each damping-wagon comprising: several wheels, one main-plate with on both sides permanently fastened several tubes, and above the main-plate permanently fastened the bottoms of several conic-springs in vertical setting which can be in fullness squeeze down, and whereat these several conic-springs tops are permanently fastened to being situated above them a middle-plate or a top-plate, and to the top plate on both sides are permanently fastened several leading-shafts, and wherein all leading-shafts are adopted to fit with several tubes in middle-plate and the main-plate; and wherein all lowered down leading-shafts are adopted to not hook up and not collide with any components of the hangers and of the deck-gantries, and each damping-wagon can comprise one or several layers of conic-springs, and each damping-wagon can comprise thick flexible-layers above the top-plate, and each damping-wagon can comprise flexible wedge-shaped-fenders on sides; and wherein all damping-wagons can precisely roll in rails on both deck-gantries tops and so transverse the ship length, and wherein all damping-wagons are adopted to place themselves with high accuracy under the landing space-rocket because these damping-wagons can precisely move transverse the ship on both deck-gantries tops, and wherein the damping-wagons can be in varies sizes, and wherein two damping-wagons are adopted to one vertically landing space-rocket which hangs itself on its spreadable-arms, and wherein the damping-wagons are adopted to be squeezed down after the space-rocket hangs itself, and wherein two squeezed down damping-wagons are adopted to roll over in rails from two deck-gantries tops onto two hangers tops, and wherein constructions of all damping-wagons are entirely adapted with constructions and function of the entire hangers and of the gantries, and wherein all damping-wagons have damping high range during hanging the space-rockets equipped with several spreadable-arms, and wherein simultaneously all damping-wagons maintain unshaken and stable top surfaces during their squeezing down by the space-rocket, and wherein two squeeze down damping-wagons with hanged space-rocket and both grasping-wagons having grasped this space-rocket bottom can move to the ship side and between one pair of hangers.
 12. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claims 1, 8, 9, 10 and 11, wherein the grasping-wagons comprising: at least two rotating-poles having spherical ends with flexible coatings, wherein the spherical ends with flexible coatings are adopted for direct contacts with the space-rockets, and wherein the grasping-wagons are low build, and wherein the grasping-wagons are adopted to completely lower down all rotating-poles on sides to horizontal setting, and wherein the grasping-wagons are adopted to move under bottom of the space-rocket which hangs itself on two deck-gantries, and wherein the grasping-wagons are adopted for blocking swinging of the landed space-rocket bottom by means of four rotating-poles, and wherein the grasping-wagons are also adopted for strong fastening of the landed space-rocket bottom, and wherein the grasping-wagons are adopted to move in rails on both movable-decks and transverse the ship, and wherein the grasping-wagons are adopted to move together in between one pair of the hangers.
 13. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claim 1, wherein the ship comprises: a few joined hulls, the horizontally movable-decks and the ballasting-wagons which all are adopted for vertical landing of the space-rockets equipped with spreadable-arms; wherein a few hulls are joined in this way that inside huge area of this ship are not any hull parts; and wherein the horizontally movable-decks are huge and installed directly above large parts of a few joined hulls, and wherein the horizontally movable-decks are adopted to be quick and entirely spread apart in two directions of this ship in order to create inside it a jumbo abyss wherein there is only sea-water, and wherein such spreading apart of these movable-decks is adopted for prevent some strike of the space-rocket which failed to stop its descent down and then this space-rocket will plunge into sea-water; and wherein the ballasting-wagons are installed inside the ship joined hulls and are placed in some tunnels which are transverse to this ship, and wherein the ballasting-wagons are adopted for very quick and precise ballasting the entire ship to perfectly horizontal position during landing each space-rocket and during moving each one on hangers, and wherein the ballasting-wagons are also adopted for continuous, quick and precise ballasting this ship during seafaring; and wherein the ship is adopted to comprise the deck-mounted landing-station for the space-rockets equipped with spreadable-arms.
 14. The utter system for multiple use of space-rockets equipped with spreadable-arms according to claim 1, wherein the harbor terminal comprises: two movable ground-gantries and can comprise the ground-crane, which all are adopted for reload, launch and vertical landing of the space-rockets equipped with spreadable-arms; and this way the harbor terminal is adopted to be the landing-station; and wherein both movable ground-gantries comprise some wheels to precisely move about on ground and turn on it. 